DOC AIRBUS | AMM A320FINDICATING/RECORDING SYSTEMS - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
This chapter covers the five main subjects:
** ON A/C NOT FOR ALL This chapter covers the five main subjects:
- Independent instruments (Ref. AMM D/O 31-21-00-00)
- Centralized fault display system (Ref. AMM D/O 31-30-00-00)
- Recording system (Ref. AMM D/O 31-30-00-00).
- Electronic Instrument System (EIS) (Ref. AMM D/O 31-60-00-00) including Electronic Flight Instrument System (EFIS) and Electronic Centralized Aircraft Monitor (ECAM) (Ref. AMM D/O 31-50-00-00).
2. Description and Operation
A. Instruments and Panels
(1) Panels
The aircraft is certificated to be operated by two crew members (two pilots).
An observer seat is installed aft of the pedestal offering maximum visibility over all panels.
Six Cathode Ray Tube (CRT) display units providing high level of flexibility in presentation of information are used for the main display functions i.e. flight guidance, navigation, engines and aircraft systems monitoring. They are 6" X 6" full color, all interchangeable. Conventional electromechanical instruments are also used to provide mainly back-up information.
The Captain's and First Officer's panels are dedicated to flight guidance and navigation information and comprise two CRT display units each, one Primary Flight Display (PFD) and one Navigation Display (ND). These two displays units are installed side by side.
The center instrument panel is dedicated to :
The center pedestal provides
The aircraft is certificated to be operated by two crew members (two pilots).
An observer seat is installed aft of the pedestal offering maximum visibility over all panels.
Six Cathode Ray Tube (CRT) display units providing high level of flexibility in presentation of information are used for the main display functions i.e. flight guidance, navigation, engines and aircraft systems monitoring. They are 6" X 6" full color, all interchangeable. Conventional electromechanical instruments are also used to provide mainly back-up information.
The Captain's and First Officer's panels are dedicated to flight guidance and navigation information and comprise two CRT display units each, one Primary Flight Display (PFD) and one Navigation Display (ND). These two displays units are installed side by side.
The center instrument panel is dedicated to :
- aircraft monitoring comprising two CRT display units, upper ECAM display unit for essential engine parameters, flap/slat position indication, fuel on board and Memo/Warning display and lower ECAM display unit for System/Status display.
- standby instruments
- landing gear control.
The center pedestal provides
- multifunction control and display units (MCDU) for navigation, AIDS and maintenance controls.
- controls for engines, flap/slat, speed brake and trims.
- radio management, ECAM, weather radar controls.
(2) Independent instruments - Electrical clock (Ref. AMM D/O 31-21-00-00)
A unique clock is installed on the main instrument panel.
This clock provides the primary time base installed in the aircraft. The UTC and date generation is transmitted to FMGC 1 and 2, FDIU and CFDIU.
In case of failure of the clock, CFDIU provides back-up for UTC with updating through MCDUs.
The clock also provides :
A unique clock is installed on the main instrument panel.
Indicating/Recording System - Electrical ClockThis clock provides the primary time base installed in the aircraft. The UTC and date generation is transmitted to FMGC 1 and 2, FDIU and CFDIU.
In case of failure of the clock, CFDIU provides back-up for UTC with updating through MCDUs.
The clock also provides :
- elapsed time function
- back-up chronometer function with local control. (The primary chronometer function is performed by EIS on each ND with remote controls for CAPT and F/O).
B. Centralized Fault Display System (Ref. 31-30-00)
This system provides a central maintenance aid which allows from the cockpit to extract the maintenance information and to initiate the various maintenance tests, at system or subsystem level.
It comprises :
One Centralized Fault Display Interface Unit (CFDIU) installed in the electronics rack which receives from the system bites all the maintenace data in a form directly meaningful.
The CFDIU is controlled from the two Multipurpose Control and Display Units (MCDU) (see ATA 22-82-00) to display BITE data results from the system and initiate maintenance tests.
The CFDIU also provides back-up time base for UTC to cover the loss of the main time base provided by the clock.
Optional features are available :
This system provides a central maintenance aid which allows from the cockpit to extract the maintenance information and to initiate the various maintenance tests, at system or subsystem level.
It comprises :
One Centralized Fault Display Interface Unit (CFDIU) installed in the electronics rack which receives from the system bites all the maintenace data in a form directly meaningful.
The CFDIU is controlled from the two Multipurpose Control and Display Units (MCDU) (see ATA 22-82-00) to display BITE data results from the system and initiate maintenance tests.
The CFDIU also provides back-up time base for UTC to cover the loss of the main time base provided by the clock.
Optional features are available :
- BITE data transmission to ground via ACARS
- Multi-use printer management in relation with the optional multi-use printer.
C. Recording System (Ref. 31-30-00)
The recording system allows to satisfy the recording regulation and will accomodate options for AIDS data collection, reporting, recording or printing.
The recording system allows to satisfy the recording regulation and will accomodate options for AIDS data collection, reporting, recording or printing.
(1) Basic recording system
Its function consists in the recording of the regulation mandatory parameters and additional basic parameters from the appropriate data systems.
The installation comprises one Flight Data Interface Unit (FDIU), one Digital Flight Data Recorder (DFDR), one three axis Linear Accelerometer (LA) and one Control Panel (CP)
Its function consists in the recording of the regulation mandatory parameters and additional basic parameters from the appropriate data systems.
The installation comprises one Flight Data Interface Unit (FDIU), one Digital Flight Data Recorder (DFDR), one three axis Linear Accelerometer (LA) and one Control Panel (CP)
- The DFDR is installed at the rear of the aircraft behind the rear bulkhead in an unpressurized area.
An Underwater Locating Beacon (ULB) is directly attached to the face of the DFDR - The FDIU is installed in the avionics compartment and the LA near the aircraft center of gravity. LA is connected to SDACs. The parameters acquired by the EIS (FWC, SDAC, DMC) are transmitted on their ARINC 429 output buses to FDIU which composes the data frame transmitted to the DFDR.
(2) AIDS Options - Data Management Unit (DMU)
It is installed in the electronics rack.
It is controlled from the Multifunction Control and Display Units (MCDU) (see ATA 22-82-00).
The DMU collects and manages all the data for AIDS. It is mainly oriented to the engine condition monitoring.
It is installed in the electronics rack.
It is controlled from the Multifunction Control and Display Units (MCDU) (see ATA 22-82-00).
The DMU collects and manages all the data for AIDS. It is mainly oriented to the engine condition monitoring.
(3) AIDS Options - Data Management Unit (part of FDIMU)
It is installed in the electronics rack.
It is controlled from the Multifunction Control and Display Units (MCDU) (see ATA 22-82-00).
The DMU part collects and manages all the data for AIDS. It is mainly oriented to the engine condition monitoring.
It is installed in the electronics rack.
It is controlled from the Multifunction Control and Display Units (MCDU) (see ATA 22-82-00).
The DMU part collects and manages all the data for AIDS. It is mainly oriented to the engine condition monitoring.
(4) Multi-use printer option
It allows to print data coming from the different possible sources (Ref. AMM D/O 31-35-00-00).
It allows to print data coming from the different possible sources (Ref. AMM D/O 31-35-00-00).
D. Electronic Instrument System (EIS)
The Electronic Instrument System comprises :
The Electronic Instrument System comprises :
The Electronic Instrument System comprises :
- The Electronic Flight Instrument System (EFIS) (Ref. 31-60)
- The Electronic Centralized Aircraft Monitor System (ECAM) (Ref. 31-50).
The Electronic Instrument System comprises :
- The Electronic Flight Instrument System (EFIS) (Ref. 31-60)
- The Electronic Centralized Aircraft Monitor System (ECAM) (Ref. 31-50).
(1) Electronic Flight Intrument System (EFIS)
The EFIS comprises the following equipment :
The EFIS comprises the following equipment :
- Two Primary Flight Displays (PFD), one for the captain, one for the first officer.
- Two Navigation Displays (ND), one for the captain, one for the first Officer.
- Two EFIS control sections located on left and right sides of the flight control unit.
- Three Display Management Computers (DMC), where DMC3 replaces DMC1 or DMC2 in case of failure of one of them.
The DMCs are installed in the avionics compartment. - Switching panel for reconfiguration purpose installed in the front part of the center pedestal.
- Display unit brightness and ON/OFF control.
- PFD/ND XFR pushbutton switch.
(a) PFD indications
The PFD format shall include the following parameters :
The PFD format shall include the following parameters :
- pitch and roll attitude
- * flight path angle and drift angle
- * flight director commands (FD bars or FPD symbol)
- actual magnetic heading and track
- * selected magnetic heading
- selected and actual speed
- * limiting and operational speeds
- selected and actual altitude
- altitude barometric correction setting
- vertical speed
- * mach number
- * radio altitude and decision height
- * final approach trajectory deviations (ILS or R-NAV)
- * marker indications
- * AFS mode annunciations.
NOTE: * Depending on pilot selection and/or A/C present flight configuration.
(b) ND indications
The ND format shall have five selectable operational modes and shall display the following parameters :
The ND format shall have five selectable operational modes and shall display the following parameters :
1 3 ROSE modes = ROSE-ILS, ROSE-VOR, ROSE-NAV
In each mode the following information shall be provided :
Course selection and lateral deviation shall be provided in VOR and ILS submodes.
A map with the actual flight path and flight plan information shall be provided in NAV mode.
Additional data including constraints, waypoints, NAVAIDS and airports may be selected.
In each mode the following information shall be provided :
- aircraft heading and track heading dial, (oriented "heading up" with the aircraft symbol in the center of the display)
- speeds (GS, TAS)
- wind data
- ADF/VOR bearing (on selection), and corresponding station characteristics (ident or frequency), plus DME distances if a VOR/DME or DME station is tuned.
Course selection and lateral deviation shall be provided in VOR and ILS submodes.
A map with the actual flight path and flight plan information shall be provided in NAV mode.
Additional data including constraints, waypoints, NAVAIDS and airports may be selected.
2 ARC mode
The following information shall be provided :
Additional data, including constraints, waypoints, NAVAIDS and airports may be selected.
The following information shall be provided :
- aircraft heading and track (oriented "heading up" with the aircraft symbol at the lower part of the display)
- map with actual flight plan and flight plan information
- speeds (GS, TAS)
- wind data
Additional data, including constraints, waypoints, NAVAIDS and airports may be selected.
3 PLAN mode
- A fixed area plan oriented "north up", centered on a selectable waypoint, shall include actual flight plan, flight plan information and aircraft position.
- Additional data including constraints, waypoints, NAVAIDS and airports may be selected.
4 chronograph function
In any of the ND operating modes it is possible to display a chronograph function operated by a dedicated pushbutton switch provided for each pilot.
In any of the ND operating modes it is possible to display a chronograph function operated by a dedicated pushbutton switch provided for each pilot.
(2) Electronic Centralized Aircraft Monitor System (ECAM)
The ECAM system comprises the following equipment :
In addition the ECAM system generates aural and visual warnings. The aural warnings are transmitted by the Cockpit Audio Loudspeakers.
The visual signals are transmitted by the DU messages and the MASTER WARN and MASTER CAUT lights.
The ECAM system comprises the following equipment :
- One upper display unit for engine/warning display
- One lower display unit for system/status display
- One ECAM control panel
- Two Flight Warning Computers (FWC)
- Two System Data Acquisition Concentrators (SDAC)
- Two MASTER WARN (MW) and two MASTER CAUT (MC) lights.
- Two Cockpit Audio Loudspeakers (CAL)
- Three DMCs common with EFIS
- engine primary indication, fuel quantity on board and flaps/slats position indication
- operational assistance for both normal and abnormal aircraft system configurations.
In addition the ECAM system generates aural and visual warnings. The aural warnings are transmitted by the Cockpit Audio Loudspeakers.
The visual signals are transmitted by the DU messages and the MASTER WARN and MASTER CAUT lights.
(a) Upper display unit
In normal operation, i.e. without DU failure, the top two thirds of the display will present engine indications, plus fuel quantity and flaps/slats position indications.
The bottom third will present :
In normal operation, i.e. without DU failure, the top two thirds of the display will present engine indications, plus fuel quantity and flaps/slats position indications.
The bottom third will present :
- either MEMO messages, i.e. a reminder of functions/systems which are temporily used (e.g. APU running).
- or MEMO messages including some key items of the normal check/list in the Take-Off and the Approach phases
- or warning/caution messages, giving the title of the failure and the corresponding procedures/actions to be performed.
(b) Lower display unit
In normal operation, the display unit will present :
In normal operation, the display unit will present :
1 either an A/C system synoptic diagram, corresponding to the current phase of flight or to the crew manual selection, or to the caution/ warning that is being shown to the crew eventually ;
2 or status messages, i.e. :
At last, the two bottom lines are reserved for the display of A/C parameters such as TAT, SAT, A/C Gross weight.
- an operational summary of the aircraft condition,
- an explanation of possible autoland capability downgrading,
- indications of the aircraft status following all failures except those that do not affect the flight,
- general contents, limitations (speed, altitude), peculiar or emergency postponable procedures, information, etc.
At last, the two bottom lines are reserved for the display of A/C parameters such as TAT, SAT, A/C Gross weight.
(3) Electronic Centralized Aircraft Monitor System (ECAM)
The ECAM system comprises the following equipment :
In addition the ECAM system generates aural and visual warnings. The aural warnings are transmitted by the Cockpit Audio Loudspeakers.
The visual signals are transmitted by the DU messages and the MASTER WARN and MASTER CAUT lights.
The ECAM system comprises the following equipment :
- One upper display unit for engine/warning display
- One lower display unit for system/status display
- One ECAM control panel
- Two Flight Warning Computers (FWC)
- Two System Data Acquisition Concentrators (SDAC)
- Two MASTER WARN (MW) and two MASTER CAUT (MC) lights.
- Two Cockpit Audio Loudspeakers (CAL)
- Three DMCs common with EFIS
- engine primary indication, fuel quantity on board and flaps/slats position indication
- operational assistance for both normal and abnormal aircraft system configurations.
In addition the ECAM system generates aural and visual warnings. The aural warnings are transmitted by the Cockpit Audio Loudspeakers.
The visual signals are transmitted by the DU messages and the MASTER WARN and MASTER CAUT lights.
(a) Upper display unit
In normal operation, i.e. without DU failure, the top two thirds of the display will present engine indications, plus fuel quantity and flaps/slats position indications.
The bottom third will present :
In normal operation, i.e. without DU failure, the top two thirds of the display will present engine indications, plus fuel quantity and flaps/slats position indications.
The bottom third will present :
- either MEMO messages, i.e. a reminder of functions/systems which are temporily used (e.g. APU running).
- or MEMO messages including some key items of the normal check/list in the Take-Off and the Approach phases
- or warning/caution messages, giving the title of the failure and the corresponding procedures/actions to be performed.
(b) Lower display unit
In normal operation, the display unit will present :
In normal operation, the display unit will present :
1 either an A/C system synoptic diagram, corresponding to the current phase of flight or to the crew manual selection, or to the caution/ warning that is being shown to the crew eventually ;
2 or status messages, i.e. :
At last, the two bottom lines are reserved for the display of A/C parameters such as TAT, SAT, A/C Gross weight.
- an operational summary of the aircraft condition,
- an explanation of possible autoland capability downgrading,
- indications of the aircraft status following all failures except those that do not affect the flight,
- general contents, limitations (speed, altitude), peculiar or emergency postponable procedures, information, etc.
At last, the two bottom lines are reserved for the display of A/C parameters such as TAT, SAT, A/C Gross weight.
(4) EIS reconfigurations
The selected architecture offers a large versatility thanks to several redundancies :
The selected architecture offers a large versatility thanks to several redundancies :
- DMC 3 can replace DMC 1 or DMC 2,
- transfers between PFD and ND images are available,
- upper ECAM DU image (Engines and Memo/Warning) can be transferred on lower ECAM DU which is normally dedicated to systems/status display,
- Upper or lower ECAM DU image can be transferred on CAPT or F/O ND,
- the two FWCs and the two SDACs are identical and are configured in such a way that all the master warnings and cautions are still operative in case of one FWC and/or SDAC failure.