DOC AIRBUS | AMM A320FFunctional Interfaces - Description and Operation
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
The control of the propulsion system consists of a Full Authority Digital Engine Control (FADEC) system for each engine and nacelle that interfaces with various aircraft (A/C) systems to provide propulsion system control and indications.
The major functional elements of engine interface consist of:
** ON A/C NOT FOR ALL The control of the propulsion system consists of a Full Authority Digital Engine Control (FADEC) system for each engine and nacelle that interfaces with various aircraft (A/C) systems to provide propulsion system control and indications.
EEC/EIU ARINC 429 InterfacesThe major functional elements of engine interface consist of:
- Electronic Engine Control (EEC)
- Engine Interface Unit (EIU)
- Air Data/Inertial Reference System (ADIRS)
- Automatic Flight System (AFS)
- Electronic Instrument System (EIS) associated to a Flight Warning System (FWS)
- Centralized Fault Display System (CFDS)
- Generator Control Unit (GCU).
2. Description
A. EEC Fuel Controlling and Governing System
There are two EECs per propulsion system installed on the A/C. The EEC contains all critical and non-critical functions such as:
In addition, the EEC communicates to the cockpit, the status of the FADEC system and its interfacing components.
For more information on fuel controlling and governing system, (Ref. AMM D/O 73-21-00-00).
There are two EECs per propulsion system installed on the A/C. The EEC contains all critical and non-critical functions such as:
- Processing of the Throttle Resolver Angle (TRA) signal
- Control of fuel flow
- Variable geometry control
- Stability bleed systems
- Performance related items (e.g. active clearance control)
- FRTT control
- Engine starting and ignition
- Thrust reverser control
- Engine vibration/health monitoring.
In addition, the EEC communicates to the cockpit, the status of the FADEC system and its interfacing components.
For more information on fuel controlling and governing system, (Ref. AMM D/O 73-21-00-00).
(1) The control of the propulsion system consists of a FADEC system for each engine and nacelle that interfaces with various A/C systems to provide propulsion system control and indications.
(a) ADIRS
Each EEC channel shall have two Aeronautical Radio Incorporated (ARINC) 429 inputs dedicate to the air data/inertial reference unit (1 and 2).
The data from the A/C includes:
Each EEC channel shall have two Aeronautical Radio Incorporated (ARINC) 429 inputs dedicate to the air data/inertial reference unit (1 and 2).
The data from the A/C includes:
- Altitude
- Total air pressure
- Total Air Temperature
- Mach number and VCAS
- A/C type, which are used to calculate the appropriate engine ratings for the flight condition.
(b) AFS
The AFS comprises of:
The AFS comprises of:
- Three Multipurpose Control Display Unit (MCDU)
- One Flight Control Unit (FCU)
- Two Flight Management and Guidance Computer (FMGC)
- Two Autothrust (A/THR) instinctive disconnect pushbuttons.
- A/THR, including alpha floor protection
- Flex Take Off (TO) temperature and derated TO and derated climb selection for corresponding FADEC thrust computation
- Go-around mode selection using throttle position given by the FADEC
- Vertical flight management using engine data
- Back-up weight computation using FADEC integrated fuel used.
(c) CFDS
The A/C CFDS offers the operator the opportunity to access information from all system Built-In Test Equipment (BITE) at a centralized point.
The CFDS consists of:
The CFDIU acquires FADEC system BITE information through the EIU on a single ARINC 429 bus.
The CFDS will have two operating modes:
The A/C CFDS offers the operator the opportunity to access information from all system Built-In Test Equipment (BITE) at a centralized point.
The CFDS consists of:
- One Centralized Fault Display Interface Unit (CFDIU)
- Two MCDUs
- One printer
- Different avionic system BITE.
The CFDIU acquires FADEC system BITE information through the EIU on a single ARINC 429 bus.
The CFDS will have two operating modes:
- Normal mode, where all systems will continuously report failures to the CFDIU.
- Interactive mode, where the CFDIU will provide a centralized means to display or interrogate BITEs of various systems and to initiate tests from the MCDUs located in the cockpit.
From the MCDU it will be possible to print maintenance or test reports.
- Engine/Warning Display (EWD)
- Electronic Centralized Aircraft Monitoring (ECAM) display unit through the Display Management Computer (DMC).
(d) Bleed Monitoring Computer (BMC)
The BMC is responsible for the monitoring of the engine bleed-air system involved in the supply of bleed air to the A/C Environmental Control System (ECS).
It will perform this function by using information from ECS valve positions and bleed air characteristics.
Among which some come from the EEC through the associated EIU on ARINC 429 data bus.
The BMC is responsible for the monitoring of the engine bleed-air system involved in the supply of bleed air to the A/C Environmental Control System (ECS).
It will perform this function by using information from ECS valve positions and bleed air characteristics.
Among which some come from the EEC through the associated EIU on ARINC 429 data bus.
(e) Spoiler Elevator Computer (SEC)
In order to prevent a thrust control malfunction due to an engine control system failure, SEC computers provide "GND/IDLE" discrete signals which are set to "ground" only if the corresponding throttle is at IDLE or in the reverse area and the opposite throttle is less than 30 degrees and the A/C is seen on ground.
These SEC "GND/IDLE" signals control A/C static relays which provide an A/C "GND/IDLE" signal used by EEC logic to allow engine shut down if simultaneously the observed thrust is exceeding a certain level and the A/C "GND/IDLE" discrete signal is at "ground".
In order to prevent a thrust control malfunction due to an engine control system failure, SEC computers provide "GND/IDLE" discrete signals which are set to "ground" only if the corresponding throttle is at IDLE or in the reverse area and the opposite throttle is less than 30 degrees and the A/C is seen on ground.
These SEC "GND/IDLE" signals control A/C static relays which provide an A/C "GND/IDLE" signal used by EEC logic to allow engine shut down if simultaneously the observed thrust is exceeding a certain level and the A/C "GND/IDLE" discrete signal is at "ground".
(f) EIS/FWS
The A/C will have an EIS, by which the A/C systems (including the FADEC system) communicate to the flight crew.
System operational data and warnings with associated procedures/recommendations through the FWS will also be available.
The A/C will have an EIS, by which the A/C systems (including the FADEC system) communicate to the flight crew.
System operational data and warnings with associated procedures/recommendations through the FWS will also be available.
1 EIS
The EIS consists mainly of three DMCs, six Display Units (DUs) and three cockpit control panels.
The propulsion system control and survey indications are displayed to the crew through the dedicated ECAM DUs: the EWD and the System Display (SD).
These indications are generated by the DMC, which manages the information transmitted directly from the EEC unit through ARINC 429 high-speed data buses.
The EIS consists mainly of three DMCs, six Display Units (DUs) and three cockpit control panels.
The propulsion system control and survey indications are displayed to the crew through the dedicated ECAM DUs: the EWD and the System Display (SD).
These indications are generated by the DMC, which manages the information transmitted directly from the EEC unit through ARINC 429 high-speed data buses.
2 FWS
The FWS will trigger the propulsion system warnings and associated crew procedures/recommendations.
The FWS is composed of Flight Warning Computer (FWC), System Data Acquisition Concentrator (SDAC), loud speakers and visual attention getters.
The FWC will gather necessary information directly from the EEC, EIU and SDAC unit through ARINC 429 high-speed data buses.
The propulsion system warning messages with the associated crew procedures/recommendations generated by the FWC will be displayed on the EWD ECAM display unit through the DMC.
The FWS will trigger the propulsion system warnings and associated crew procedures/recommendations.
The FWS is composed of Flight Warning Computer (FWC), System Data Acquisition Concentrator (SDAC), loud speakers and visual attention getters.
The FWC will gather necessary information directly from the EEC, EIU and SDAC unit through ARINC 429 high-speed data buses.
The propulsion system warning messages with the associated crew procedures/recommendations generated by the FWC will be displayed on the EWD ECAM display unit through the DMC.
3 GCU
The GCU Bus is a high speed bus and not a low speed bus.
One high-speed A429 bus from the GCU is available at the EIU interface (GCU1 to EIU1 / GCU2 to EIU2).
The GCU Bus is a high speed bus and not a low speed bus.
One high-speed A429 bus from the GCU is available at the EIU interface (GCU1 to EIU1 / GCU2 to EIU2).
(g) EIU
The EIU interfaces with various A/C computers and controls (and the associated propulsion system control) to perform the following main functions:
Each EIU communicates with the associated EEC system through ARINC 429 high-speed digital data bus.
The EIU interfaces with various A/C computers and controls (and the associated propulsion system control) to perform the following main functions:
- Transmission of cockpit panel and A/C computer data to the associated EEC.
- Internal processing of some airframe status signals needed by the EEC system (bleed configuration, approach idle selection, etc.) and conversely, of engine status signals needed by airframe systems.
- Control of airframe electrical supplies to the FADEC system.
- Engine-to-engine segregation.
- Control of power to the heater and the hydraulic depressurization solenoid.
Each EIU communicates with the associated EEC system through ARINC 429 high-speed digital data bus.
(1) EIU Discrete Inputs
(a) From the A/C to the EIU
- Master Lever ON
- Master Lever OFF
- Rotary Selector IGNITION
- Rotary Selector NORM
- Rotary Selector CRANK
- Wing De ICING OFF
- Nacelle Anti Ice OFF Own
- Nacelle Anti Ice ON Opposite
- Fire handle
- Oil Low Press
- Eng Man Start
- Airframe FADEC Supply ON
- Left Hand Landing Gear Compressed
- Right Hand Landing Gear Compressed
- Nose Landing Gear Compressed
- Ground Spoiler Out from SEC
- Flaps and Slats Lever in Retracted Position
- Flaps above 19 Degrees
- TLA
- FRSOV Selected OFF
- Dataloading Enable
- ENGINE 1 POSITION
- ENGINE 2 POSITION
- Pin Prog CFM Leap-1A
- Pin Prog GTF
- APU Master Switch ON
- APU Master Switch OFF
- Prox_sw_number_HPP
- A/C has BRL Option1 option installed (HPP)
- ”Dual Cooling” pushbutton is pressed
- A/C has BRL Envelope option installed (HPP)
- APU Honeywell Type (HPP) (Preboost Disabled) (post EIU software FCS 4.3)
- Pin Prog EEC Channels Power supply Crossed (HPP) (post EIU software EIU 4.3)
- APU Honeywell Type (HPP) (ICARE Enabled) (post EIU software FCS 4.3).
(b) From the Engine to the EIU
- Door Latch Monitoring Prox Switch 1– position
- Door Latch Monitoring Prox Switch 2– position
- Door Latch Monitoring Prox Switch 3– position.
(2) EIU Discrete Output
(a) List of discrete outputs 28VDC/OPEN:
- TLS 115 Unlock
- Flight Lock Doors
- APU BOOST Command 1
- APU BOOST Command 2
- Master Lever Light Fault ”ON”
- Oil Low pressure and Ground 1
- Oil Low pressure and Ground 2
(b) List of Discrete outputs GROUND/OPEN:
- HPSOV Closed
- N2 Not Below Idle
- TLA in Take Off Position
- Start Valve Closure
- NAI P/B Fault Light (Feedback).
3. BITE Test
A. EIU Interactive Mode
(1) The CFDS enables to get maintenance information from the EIU.
It is the interactive mode of the EIU.
The interactive mode provides the ability to establish an interactive dialogue with the EIU by means of menus on one MCDU screen.
It is the interactive mode of the EIU.
The interactive mode provides the ability to establish an interactive dialogue with the EIU by means of menus on one MCDU screen.
(a) The interactive mode can only be entered on ground and when the engine is shut down.
(b) The interactive mode is initiated when EIU key is selected on the menu of the SYSTEM REPORT/TEST/ENG page of the MCDU.
Only one EIU is selectable at one time.
Only one EIU is selectable at one time.
(2) Tests:
(a) System Test:
This test displays all the class 1, 2 and 3 faults detected by the EIU during the test.
This test displays all the class 1, 2 and 3 faults detected by the EIU during the test.
(b) Ground Scanning:
This test displays in real time all failures detected by the system without a predetermined time frame.
It allows the maintenance operator to check which failures are detected following such or such particular action.
For example to troubleshoot intermittent failures (such failures, displayed in the last leg report, may not be detected by the system test).
The maintenance operator can perform particular actions on the given system to find the conditions in which this particular intermittent failure can appear.
This test displays in real time all failures detected by the system without a predetermined time frame.
It allows the maintenance operator to check which failures are detected following such or such particular action.
For example to troubleshoot intermittent failures (such failures, displayed in the last leg report, may not be detected by the system test).
The maintenance operator can perform particular actions on the given system to find the conditions in which this particular intermittent failure can appear.
(c) Discrete Inputs Report:
This report indicates the status of all the EIU discrete inputs.
This report indicates the status of all the EIU discrete inputs.
(d) Discrete Outputs Simulation:
This menu allows to change the status of the EIU discrete outputs.
This menu allows to change the status of the EIU discrete outputs.
(3) Fault Reports:
The interactive mode generates the following fault reports:
The interactive mode generates the following fault reports:
(a) Last Leg Report:
This report displays all the class 1 and 2 faults detected by the EIU during the last flight.
This report displays all the class 1 and 2 faults detected by the EIU during the last flight.
(b) Previous Leg Report:
This report displays all the class 1 and 2 faults detected by the EIU during up to the last 63 flights previous to the last flight.
This report displays all the class 1 and 2 faults detected by the EIU during up to the last 63 flights previous to the last flight.
(c) Ground Report:
This report displays the list of all maintenance messages memorized on ground since the last flight to ground transition.
The ground report is used to troubleshoot new failures detected since the A/C has landed.
As only failures internal to the system are stored (in order to avoid spurious messages related to maintenance operation on other systems), the ground report is thus limited to internal failures.
This report displays the list of all maintenance messages memorized on ground since the last flight to ground transition.
The ground report is used to troubleshoot new failures detected since the A/C has landed.
As only failures internal to the system are stored (in order to avoid spurious messages related to maintenance operation on other systems), the ground report is thus limited to internal failures.
(d) Class 3 Faults Report:
This report displays all the class 3 faults detected by the EIU during the last flight.
This report displays all the class 3 faults detected by the EIU during the last flight.
(4) Other Reports
(a) Line Replaceable Unit identification Report
This report displays all the configuration information for the EIU.
This report displays all the configuration information for the EIU.
(b) Troubleshooting Data Report
This report displays data associated to the faults displayed in last Leg and previous legs reports.
This report displays data associated to the faults displayed in last Leg and previous legs reports.
B. EEC Interactive Mode
4. Power Supply