DOC AIRBUS | AMM A320FEIS - SWITCHING - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
The EIS reconfiguration function is part of the Electronic Instrument System (EIS) which is described in 316000.
This function is necessary to cope with availability objectives.
This reconfiguration function is mainly aimed at changing the six displays of the main instrument panel whenever necessary. These displays are:
(Ref. 316000 for further definition)
Three Display Management Computers (DMCs) drive the displays.
The EIS reconfiguration function is achieved by means of a set of switching devices plus some software implements within the DMC to enable reconfiguration of these system parts which include a failed component.
Various reconfiguration possibilities are provided in the EIS in order to cope with the operational requirements in case of failure of:
A set of switching devices and some automatic processes are provided to the crew. They are:
The EIS reconfiguration function is part of the Electronic Instrument System (EIS) which is described in 316000.
This function is necessary to cope with availability objectives.
This reconfiguration function is mainly aimed at changing the six displays of the main instrument panel whenever necessary. These displays are:
(Ref. 316000 for further definition)
- the Primary Flight Display (PFD): all information related to the behavior of the aircraft with respect to pitch and roll axes.
- the Navigation Display (ND): all information related to the behavior of the aircraft with respect to yaw axis describing the aircraft horizontal situation.
- the Engine/Warning Display (EWD):
. ENGINE area: engine parameters fuel on board slat and flap position indication. . WARNING area: all equipment failures together with their consequences on the flight. - the System/Status Display (SD): a sketch of the main aircraft systems with a symbology relating the behavior of most of the items of equipment concerned by the system.
Three Display Management Computers (DMCs) drive the displays.
The EIS reconfiguration function is achieved by means of a set of switching devices plus some software implements within the DMC to enable reconfiguration of these system parts which include a failed component.
Various reconfiguration possibilities are provided in the EIS in order to cope with the operational requirements in case of failure of:
- a bus input
- a DMC
- a DU
- a control panel (EFIS control panel of the Flight Control Unit (FCU) or ECAM control panel).
A set of switching devices and some automatic processes are provided to the crew. They are:
EIS Switching - Reconfiguration principles- One EIS DMC selector switch, to provide the change over DMC1 to DMC3 or DMC2 to DMC3.
- Two PFD/ND pushbutton switches, one on the Captain side, the other on the First Officer side
- One ECAM/ND selector switch for ECAM/CAPT ND or ECAM/F/O ND transfer.
- automatic DU switching available after a PFD DU fault or an EWD DU fault.
A. Power Supply Reconfiguration
The power supply system also enables some reconfigurations when some supply sources are missing.
Ref. chap. 24-24-00 for description of busbar reconfigurations.
The power supply system also enables some reconfigurations when some supply sources are missing.
Ref. chap. 24-24-00 for description of busbar reconfigurations.
B. Source Reconfiguration
Some sources are reconfigured manually (flight management - air data - inertial reference ), some others are reconfigured automatically (flight guidance - radio altimeter).
Some input sources are fully redundant (engine sources), whereas some others loss their data when they fail (CFDIU).
Some sources are reconfigured manually (flight management - air data - inertial reference ), some others are reconfigured automatically (flight guidance - radio altimeter).
Some input sources are fully redundant (engine sources), whereas some others loss their data when they fail (CFDIU).
C. Reconfiguration in Case of an EIS Component Failure
In order to achieve satisfactory redundancy of the system the following principles have been adopted:
In order to achieve satisfactory redundancy of the system the following principles have been adopted:
(1) A reconfiguration takes place only when:
In all cases manual switching has priority over automatic switching.
- the DMC which drives a display unit is faulty
- a DU is faulty (or switched off).
In all cases manual switching has priority over automatic switching.
(2) DMC source reconfiguration
When one DMC normal source is faulty, the crew select the DMC3 source, manually.
The DMC which drives the CAPT PFD and ND is the DMC1 or the DMC3 according to the selector switch position EIS DMC of the switching panel:
When one DMC normal source is faulty, the crew select the DMC3 source, manually.
The DMC which drives the CAPT PFD and ND is the DMC1 or the DMC3 according to the selector switch position EIS DMC of the switching panel:
- when the EIS DMC selector switch is in the NORM position then, the DMC1 is the data source for the PFD CAPT and the ND CAPT. The DMC2 is the data source for the PFD F/O and the ND F/O.
- when the EIS DMC selector switch is in the position CAPT 3 then the DMC3 is the data source for the PFD CAPT and the ND CAPT, replacing the DMC1.
- when the EIS DMC selector switch is in the position F/O 3 then, the DMC3 is the data source for the PFD F/O and the ND F/O, replacing the DMC2.
(3) EFIS REVERSE mode
In some cases it is necessary to exchange the PFD and the ND. This is the EFIS reverse mode.
Furthermore, a PFD/ND transfer occurs to satisfy priority of the PFD over the ND.
The PFD and ND images are then exchanged.
The reverse mode takes place when the PFD DU is no more valid but the ND DU is still valid.
The reverse mode can also occur on crew request.
When a reverse mode occurs automatically, the previous normal mode is not automatically recovered if the PFD DU condition turns back to normal. But, if the reverse mode is manually (or automatically) requested, a new request reverts PFD/ND configuration to normal.
In some cases it is necessary to exchange the PFD and the ND. This is the EFIS reverse mode.
Furthermore, a PFD/ND transfer occurs to satisfy priority of the PFD over the ND.
The PFD and ND images are then exchanged.
The reverse mode takes place when the PFD DU is no more valid but the ND DU is still valid.
The reverse mode can also occur on crew request.
When a reverse mode occurs automatically, the previous normal mode is not automatically recovered if the PFD DU condition turns back to normal. But, if the reverse mode is manually (or automatically) requested, a new request reverts PFD/ND configuration to normal.
(4) ECAM source switching
The ECAM displays normally select the DMC1 (or the DMC3 if manually selected) as a data source, but in the following cases the EWD and SD select the DMC2 (or the DMC3 if manually selected on the F/O side):
The ECAM displays normally select the DMC1 (or the DMC3 if manually selected) as a data source, but in the following cases the EWD and SD select the DMC2 (or the DMC3 if manually selected on the F/O side):
- the DMC1 (or DMC3) is faulty on the Captain's side (the First Officer side being still valid),
- an ECAM/ND XFR has been selected on the First Officer side and the DMC2 (or DMC3) is not faulty.
(5) ECAM REVERSE mode
In some cases it is necessary to exchange the EWD and the SD. This is the ECAM reverse mode.
The ECAM reverse mode occurs automatically when the EWD DU is no more valid but the SD DU is still valid.
If the EWD DU becomes valid again, the normal mode is not automatically recovered. It can be manually requested if the pilot switches off the EWD DU and on again, or if he switches the DU to the other DMC.
In some cases it is necessary to exchange the EWD and the SD. This is the ECAM reverse mode.
The ECAM reverse mode occurs automatically when the EWD DU is no more valid but the SD DU is still valid.
If the EWD DU becomes valid again, the normal mode is not automatically recovered. It can be manually requested if the pilot switches off the EWD DU and on again, or if he switches the DU to the other DMC.
(6) ECAM/ND transfer
This transfer enables to show one of the ECAM displays on one ND DU, on crew request.
This transfer enables to show one of the ECAM displays on one ND DU, on crew request.
(7) ECAM single display mode
The single display mode occurs when only one DU is available to show both ECAM displays.
In the single display mode the EWD is preferably displayed but a system page is available when the crew push the related key on the ECAM control panel.
The single display mode takes place automatically when only one DU is available for ECAM function. Then the EWD is displayed in priority on the single DU and the SD is available on request.
The single display mode occurs when only one DU is available to show both ECAM displays.
In the single display mode the EWD is preferably displayed but a system page is available when the crew push the related key on the ECAM control panel.
The single display mode takes place automatically when only one DU is available for ECAM function. Then the EWD is displayed in priority on the single DU and the SD is available on request.
D. EIS Reconfiguration Devices
The reconfiguration function includes:
These devices allow to cope with:
The reconfiguration function includes:
- a set of pushbutton switches, selector switches and potentiometers to enable the crew manual action
- a internal relays (inside the DMC)
- some software processes implemented in the general application software
These devices allow to cope with:
- a single DMC failure
- a dual DMC failure
- a single DU failure
- a dual DU failure
- a triple DU failure
2. Compnent Location
** ON A/C NOT FOR ALL | ------------------------------------------------------------------------------- |
| FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA |
| I I I I DOOR I REF. |
| ------------------------------------------------------------------------------- |
| 18WT SEL SW-EIS DMC, 8VU 210 3168 |
| 19WT SEL SW-ECAM/ND XFR 8VU 210 3168 |
| 9WT1 P/BSW-PFD/ND XFR, CAPT 301VU 211 3168 |
| 9WT2 P/BSW-PFD/ND XFR, F/O 500VU 212 3168 |
| 1WT1 DMC-1 85VU 127 3162 |
| 1WT2 DMC-2 86VU 126 3162 |
| 1WT3 DMC-3 85VU 127 3162 |
| 6WT CTL PNL-ECAM 11VU 210 3161 |
| 2WT1 DU-PFD, CAPT 3VU 211 3161 |
| 2WT2 DU-PFD, F/O 5VU 212 3161 |
| 4WT1 DU-EWD 4VU 210 3161 |
| 4WT2 DU-SD 5VU 212 3161 |
| 3WT1 DU-ND, CAPT 3VU 211 3161 |
| 3WT2 DU-ND, F/O 5VU 212 3161 |
| 7WT1 POT-PFD, CAPT 301VU 211 3168 |
| 7WT2 POT-PFD, F/O 500VU 212 3168 |
| 8WT1 POT-ND, CAPT 301VU 211 3168 |
| 8WT2 POT-ND, F/O 500VU 212 3168 |
3. System Description
A. Power Supply Reconfiguration
In most cases all the EIS components are supplied with 115VAC/400Hz.
This is the case when one generator only is available, and also when only the APU generator is available.
In case of a loss of the main generation, some EIS components are no longer energized. However, some of them are supplied by the emergency network and are still available as follows:
In most cases all the EIS components are supplied with 115VAC/400Hz.
This is the case when one generator only is available, and also when only the APU generator is available.
In case of a loss of the main generation, some EIS components are no longer energized. However, some of them are supplied by the emergency network and are still available as follows:
- When the EIS DMC is selected to CAPT DMC3 and the normal supply is not available, the DMC3 is then supplied by the emergency network. The PFD CAPT, the ND CAPT, the EWD is then available.
- When the normal supply for the First Officer is not available, the F/O PFD, the F/O ND, the SD are not available any more.
B. DMC Input Sources Reconfiguration
All the input reconfigurations are described in 316200 (interface)
All the input reconfigurations are described in 316200 (interface)
C. DMC Sources Reconfiguration
When one DMC fails, the two remaining computers can control the six DUs, provided the crew has selected the DMC3 which stands as a hot spare ready to take over.
When one DMC fails, the two remaining computers can control the six DUs, provided the crew has selected the DMC3 which stands as a hot spare ready to take over.
(1) Single DMC failure
(a) DMC1 failure
When the DMC1 fails, the message "INVALID DATA" is displayed on the CAPT PFD and ND and a single warning message is activated on the EWD.
The switching is manual. The Captain switches over his EFIS displays to the DMC3 source by means of the EIS DMC selector switch on the switching panel. This selector switch is normally on the NORM position. The pilot selects the CAPT/3 position and the EFIS images are valid again on the CAPT PFD and the CAPT ND.
When the DMC1 fails, the message "INVALID DATA" is displayed on the CAPT PFD and ND and a single warning message is activated on the EWD.
The switching is manual. The Captain switches over his EFIS displays to the DMC3 source by means of the EIS DMC selector switch on the switching panel. This selector switch is normally on the NORM position. The pilot selects the CAPT/3 position and the EFIS images are valid again on the CAPT PFD and the CAPT ND.
(b) DMC2 failure
As for the Captain, the F/O PFD and ND display the message "INVALID DATA". This means that the DMC2 has failed. A single warning message is triggered on the EWD. The First Officer switches over his EFIS displays to the DMC3 source by means of the EIS DMC selector switch on the switching panel. This selector switch is normally on the NORM position. The pilot selects the F/O 3 position and the EFIS images are valid again on the F/O PFD and the F/O ND.
As for the Captain, the F/O PFD and ND display the message "INVALID DATA". This means that the DMC2 has failed. A single warning message is triggered on the EWD. The First Officer switches over his EFIS displays to the DMC3 source by means of the EIS DMC selector switch on the switching panel. This selector switch is normally on the NORM position. The pilot selects the F/O 3 position and the EFIS images are valid again on the F/O PFD and the F/O ND.
(c) DMC3 failure
When the DMC3 fails, a single warning message is then displayed on the EWD to indicate this DMC3 fault. No EFIS or ECAM image is affected by the DMC3 failure.
The switching to DMC3 is then not possible.
When the DMC3 fails, a single warning message is then displayed on the EWD to indicate this DMC3 fault. No EFIS or ECAM image is affected by the DMC3 failure.
The switching to DMC3 is then not possible.
(2) Dual DMC failure
(a) Dual DMC1 + DMC3 failure
If the Captain switches over his EFIS display to the DMC3 source and cannot recover a correct EFIS display, this means that neither the DMC1 nor the DMC3 is available for EFIS display. The First Officer EFIS displays are still available together with the ECAM display: the DMC2 takes over automatically. But the Captain can rely only on the set of standby instruments.
If the Captain switches over his EFIS display to the DMC3 source and cannot recover a correct EFIS display, this means that neither the DMC1 nor the DMC3 is available for EFIS display. The First Officer EFIS displays are still available together with the ECAM display: the DMC2 takes over automatically. But the Captain can rely only on the set of standby instruments.
(b) Dual DMC2 + DMC3 failure
In this case, the F/O PFD and ND are no longer driven and display a message: "INVALID DATA".
Since the F/O EFIS displays are not available any more with the EIS DMC selector switch in the F/O 3 position the First Officer rely on the standby instruments while the ECAM display is still available.
In this case, the F/O PFD and ND are no longer driven and display a message: "INVALID DATA".
Since the F/O EFIS displays are not available any more with the EIS DMC selector switch in the F/O 3 position the First Officer rely on the standby instruments while the ECAM display is still available.
(c) Dual DMC1 + DMC2 failure
In this case the CAPT and F/O EFIS displays are not available. Neither is the ECAM display available. One pilot must place the EIS DMC selector switch to the position CAPT 3, or F/O 3 to have his PFD and ND driven by the DMC3, together with the ECAM display which becomes available again.
In the position CAPT 3 the PFD and ND of the First Officer side display the message: INVALID DATA.
In the position F/O 3 the PFD and ND of the Captain side display the message: INVALID DATA.
In this case the CAPT and F/O EFIS displays are not available. Neither is the ECAM display available. One pilot must place the EIS DMC selector switch to the position CAPT 3, or F/O 3 to have his PFD and ND driven by the DMC3, together with the ECAM display which becomes available again.
In the position CAPT 3 the PFD and ND of the First Officer side display the message: INVALID DATA.
In the position F/O 3 the PFD and ND of the Captain side display the message: INVALID DATA.
(3) Triple DMC failure
In case of triple DMC failure, the PFDs and NDs are no longer available. The pilots use the standby indicators:
In case of triple DMC failure, the PFDs and NDs are no longer available. The pilots use the standby indicators:
- Standby airspeed indicator (401VU)
- Standby altimeter (401VU) next to the upper display unit
- Standby horizon
- DDRMI (401VU) next to the lower display unit
- Standby compass (top of the windshield center post)
- Angle of attack indicator (optional).
D. Reconfiguration in Case of DU Failure
(1) EFIS DU failure
The Captain's PFD/ND XFR pushbutton switch and the First Officer's PFD/ND XFR pushbutton switch enable to exchange the PFD and the ND. This is a manual way to recover one missing EFIS display.
The Captain's PFD/ND XFR pushbutton switch and the First Officer's PFD/ND XFR pushbutton switch enable to exchange the PFD and the ND. This is a manual way to recover one missing EFIS display.
(a) PFD DU failure
When the PFD DU fails, the PFD is automatically transferred to the ND DU as the DMC swaps its PFD and ND outputs. However there is no automatic switching back when the PFD DU becomes valid again.
When the PFD DU is manually switched off, the same display transfer applies.
If the pilot needs his ND on the ND DU he can call it back if he pushes the PFD/ND pushbutton switch.
This applies to the CAPT or the F/O PFD.
When the PFD DU fails, the PFD is automatically transferred to the ND DU as the DMC swaps its PFD and ND outputs. However there is no automatic switching back when the PFD DU becomes valid again.
When the PFD DU is manually switched off, the same display transfer applies.
If the pilot needs his ND on the ND DU he can call it back if he pushes the PFD/ND pushbutton switch.
This applies to the CAPT or the F/O PFD.
(b) ND DU failure
When the ND DU fails, the ND can be manually recovered on the PFD DU when the pilot pushes the PFD/ND pushbutton switch.
When the ND DU fails, the ND can be manually recovered on the PFD DU when the pilot pushes the PFD/ND pushbutton switch.
(2) ECAM DU failure
(a) EWD DU failure
When the EWD DU fails, the EWD is automatically transferred to the SD DU. The same transfer applies when the EWD DU is switched off. In that case only one DU is available to show two ECAM displays. This mode is called the SINGLE DISPLAY mode.
If the pilot needs his SD on the SD DU, he must push the related system key on the ECAM control panel. When the key is released, the EWD is displayed again.
If the pilot changes the position of the ECAM/ND XFR selector switch, both ECAM displays can be shown:
When the EWD DU fails, the EWD is automatically transferred to the SD DU. The same transfer applies when the EWD DU is switched off. In that case only one DU is available to show two ECAM displays. This mode is called the SINGLE DISPLAY mode.
If the pilot needs his SD on the SD DU, he must push the related system key on the ECAM control panel. When the key is released, the EWD is displayed again.
If the pilot changes the position of the ECAM/ND XFR selector switch, both ECAM displays can be shown:
- the EWD on the SD DU (automatically)
- the SD on the ND DU (CAPT or F/O, according to the position of the ECAM/ND selector switch).
(b) SD DU failure
When the SD DU fails, the EWD DU takes over the presentation of both ECAM displays. As previously described this is the SINGLE DISPLAY mode where an ECAM system page is available on request.
The DUAL DISPLAY mode is available when the pilot transfers the SD to his ND DU by means of the ECAM/ND XFR selector switch on the SWITCHING panel.
The missing ND can then be called up on the PFD DU by means of the PFD/ND pushbutton switch and exchanged again with the PFD if the PFD/ND pushbutton switch is pushed again. The ND DU presents the ECAM display as long as the ECAM/ND selector switch is in the CAPT or F/O position.
When the SD DU fails, the EWD DU takes over the presentation of both ECAM displays. As previously described this is the SINGLE DISPLAY mode where an ECAM system page is available on request.
The DUAL DISPLAY mode is available when the pilot transfers the SD to his ND DU by means of the ECAM/ND XFR selector switch on the SWITCHING panel.
The missing ND can then be called up on the PFD DU by means of the PFD/ND pushbutton switch and exchanged again with the PFD if the PFD/ND pushbutton switch is pushed again. The ND DU presents the ECAM display as long as the ECAM/ND selector switch is in the CAPT or F/O position.
(3) Dual ECAM DU failure
In case both ECAM DUs fail, the pilot can retrieve the EWD and the SD in turn on the ND DU by means of the ECAM/ND XFR selector switch. The mode used is the SINGLE DISPLAY mode as there is only one DU available for the whole ECAM function.
In case both ECAM DUs fail, the pilot can retrieve the EWD and the SD in turn on the ND DU by means of the ECAM/ND XFR selector switch. The mode used is the SINGLE DISPLAY mode as there is only one DU available for the whole ECAM function.
E. Table of Reconfigurations
The table below gives the main reconfigurations with respect to the position of the switching selector switches.
The table below gives the main reconfigurations with respect to the position of the switching selector switches.
NOTE: EWD* =System page display replaces the EWD when a system page is selected on the ECAM control panel
| ---------------------------------------------------------------------------- |
| !FAULT !FAULTY !SELECTED SWITCHING ! IMAGE DISPLAYED !n°! |
| !TYPE !ITEM !----------------------!--------------------------------- |
| ! ! !PFD! EIS !ECAM/ND !CAPT EFIS! ECAM !F/O EFIS ! ! |
| ! ! !/ND! DMC ! XFR !---------!---------!---------! ! |
| ! ! !XFR! SEL ! !PFD ! ND !EWD ! SD ! ND !PFD ! ! |
| !-------------------!C F!C3 N F3 ! C N F !--------------------------------! |
| !NORMAL !NORMAL ! ! N ! N !PFD1!ND1 !EWD1!SD1 !ND2 !PFD2! 1! |
| !NORMAL !NORMAL !C ! N ! N !ND1 !PFD1!EWD1!SD1 !ND2 !PFD2! 2! |
| !NORMAL !NORMAL ! F! N ! N !PFD1!ND1 !EWD1!SD1 !PFD2!ND2 ! 3! |
| !NORMAL !NORMAL !C F! N ! N !ND1 !PFD1!EWD1!SD1 !PFD2!ND2 ! 4! |
| !ONE EFIS!PFD1 ! ! N ! N ! nil!PFD1!EWD1!SD1 !ND2 !PFD2! 5! |
| !DU FAULT!PFD2 ! ! N ! N !PFD1!ND1 !EWD1!SD1 !PFD2! nil! 6! |
| ! !ND1 ! ! N ! N !PFD1!nil !EWD1!SD1 !ND2 !PFD2! 7! |
| ! !ND2 ! ! N ! N !PFD1!ND1 !EWD1!SD1 !nil !PFD2! 8! |
| !2 EFIS !PFD1+ND1 ! ! N ! N ! nil! nil!EWD1!SD1 !ND2 !PFD2! 9! |
| !DU FAULT!PFD2+ND2 ! ! N ! N !PFD1!ND1 !EWD1!SD1 ! nil! nil!10! |
| ! !PFD1+PFD2 ! F! N ! N ! nil!PFD1!EWD1!SD1 !ND2 ! nil!11! |
| ! !PFD1+PFD2 !C ! N ! N ! nil!ND1 !EWD1!SD1 !PFD2! nil!12! |
| ! !ND1+ND2 ! F! N ! N !PFD1! nil!EWD1!SD1 ! nil!ND2 !13! |
| ! !ND1+ND2 !C ! N ! N !ND1 ! nil!EWD1!SD1 ! nil!PFD2!14! |
| !3 EFIS !PFD1+PFD2+! ! N ! N ! nil!PFD1!EWD1!SD1 ! nil! nil!15! |
| !DU FAULT! ND2 !C ! N ! N ! nil!ND1 !EWD1!SD1 ! nil! nil!16! |
| !1 ECAM !EWD ! ! N ! N !PFD1!ND1 ! nil!EWD*!ND2 !PFD2!17! |
| !DU FAULT!EWD ! ! N !C !PFD1!SD1 ! nil!EWD1!ND2 !PFD2!18! |
| ! !EWD ! ! N ! F !PFD1!ND1 ! nil!EWD1!SD2 !PFD2!19! |
| ! !EWD !C ! N !C !ND1 !SD1 ! nil!EWD1!ND2 !PFD2!20! |
| !2 ECAM !EWD+SD ! ! N ! N !PFD1!ND1 ! nil! nil!ND2 !PFD2!21! |
| !DU FAULT!EWD+SD ! ! N !C !PFD1!EWD*! nil! nil!ND2 !PFD2!22! |
| ! !EWD+SD !C ! N !C !ND1 !EWD*! nil! nil!ND2 !PFD2!23! |
| ! !EWD+SD ! F! N ! F !PFD1!ND1 ! nil! nil!EWD*!ND2 !24! |
| ! 1 DMC !DMC1 ! ! N ! N ! nil! nil!EWD2!SD2 !ND2 !PFD2!25! |
| ! FAULT !DMC1 ! !C3 ! N !PFD3!ND3 !EWD3!SD3 !ND2 !PFD2!26! |
| ! !DMC2 ! ! N ! N !PFD1!ND1 !EWD1!SD1 ! nil! nil!27! |
| ! !DMC2 ! ! F3! !PFD1!ND1 !EWD1!SD1 !ND3 !PFD3!28! |
| ! 2 DMC !DMC1+DMC2 ! ! N ! N ! nil! nil! nil! nil! nil! nil!29! |
| ! FAULT !DMC1+DMC2 ! !C3 ! N !PFD3!ND3 !EWD3!SD3 ! nil! nil!30! |
| ! !DMC1+DMC2 ! ! F3! N ! nil! nil!EWD3!SD3 !PFD3!ND3 !31! |
NOTE: SELECTED SWITCHING:
PFD/ND XFR-C : CAPT PFD/ND pushbutton switch pushed
PFD/ND XFR-F : F/O PFD/ND pushbutton switch pushed
EIS DMC SEL -N : EIS DMC selector switch in NORM position
EIS DMC SEL -C3: EIS DMC selector switch in position CAPT/3
EIS DMC SEL -F3 : EIS DMC selector switch in position F/OFF/3
ECAM/ND XFR-N : ECAM/ND selector switch in NORM position
ECAM/ND XFR-C : ECAM/ND selector switch in CAPT position
ECAM/ND XFR-F : ECAM/ND selector switch in F/O position
PFD/ND XFR-C : CAPT PFD/ND pushbutton switch pushed
PFD/ND XFR-F : F/O PFD/ND pushbutton switch pushed
EIS DMC SEL -N : EIS DMC selector switch in NORM position
EIS DMC SEL -C3: EIS DMC selector switch in position CAPT/3
EIS DMC SEL -F3 : EIS DMC selector switch in position F/OFF/3
ECAM/ND XFR-N : ECAM/ND selector switch in NORM position
ECAM/ND XFR-C : ECAM/ND selector switch in CAPT position
ECAM/ND XFR-F : ECAM/ND selector switch in F/O position
NOTE: IMAGE DISPLAYED:
The figure 1, 2 or 3 indicates which DMC drives the display.
The figure 1, 2 or 3 indicates which DMC drives the display.
F. Functional Description
The part of the EIS dedicated to the reconfiguration function comprises:
The part of the EIS dedicated to the reconfiguration function comprises:
- a manual part which includes selector switches, pushbutton switches and potentiometers accessible to the pilot's hand
- a software process, part of the DMC application program.
(1) Manual part
This part includes various selector switches, pushbutton switches and potentiometers:
This part includes various selector switches, pushbutton switches and potentiometers:
- selector switch 18WT
This selector switche enables the Captain or the First Officer to switch the EIS DMC sources to the DMC3.
- selector switch 19WT
This selector switch enables the Captain or the First Officer to switch the ECAM image onto the ND
- pushbutton switches 9WT1 and 9WT2
These pushbutton switches enable the Captain and the First Officer to exchange the EFIS displays.
They have one stable position and one unstable position. The unstable position activates a ground to the DMC inputs.
- PFD potentiometers 7WT1 and 7WT2 and ND potentiometers 8WT1 and 8WT2
These potentiometers are provided with an end of travel switch which generates a ground to the DMC at the OFF position.
- ECAM/UPPER DISPLAY potentiometer and ECAM/LOWER DISPLAY potentiometer
These potentiometers are of the same type as the PFD and ND potentiometers. Their end of travel switch generates a ground to the DMC at the OFF position.
They are included in the ECAM control panel.
(2) Switching inside the DMC
Switching is achieved by software: the DMC provides several busses to the DUs with only two normally validated by two booleans on the bus. The other busses are validated in case of reconfiguration.
Furthermore, each active DMC receives the output busses from the DMC3, the active DMC replaces its output busses by the incoming DMC3 busses, to ensure data supply to the DUs when the active DMC has failed.
Switching is achieved by software: the DMC provides several busses to the DUs with only two normally validated by two booleans on the bus. The other busses are validated in case of reconfiguration.
Furthermore, each active DMC receives the output busses from the DMC3, the active DMC replaces its output busses by the incoming DMC3 busses, to ensure data supply to the DUs when the active DMC has failed.
(3) DMC software process
The software process related to the reconfiguration is implemented in the DMC general application software program in a dedicated memory inside the DMC and accessible by the data loader.
It includes the addressing process which validate the relevant output busses A629 according to the reconfiguration status.
The software process related to the reconfiguration is implemented in the DMC general application software program in a dedicated memory inside the DMC and accessible by the data loader.
It includes the addressing process which validate the relevant output busses A629 according to the reconfiguration status.
- the exchange of the PFD and the ND used for the EFIS transfer
- the exchange of the two ECAM displays used to save the EWD in case of a DU failure
- the computation of the ECAM single display mode used in case of an ECAM DU failure.
(4) Direct line switching
This figure represents the direct lines: from the DMC to the DU, and the return lines from the DU to the DMC.
This figure represents the direct lines: from the DMC to the DU, and the return lines from the DU to the DMC.
(5) Return line switching
Each DMC receives a return line from all the DUs it can potentially drive.
The switching of these lines depends on the reconfiguration status.
The comparison between the return line and the direct line is as follows:
Each DMC receives a return line from all the DUs it can potentially drive.
The switching of these lines depends on the reconfiguration status.
The comparison between the return line and the direct line is as follows:
| ------------------------------------------------------------------------------ |
| RETURN the DMC compares by software computation with: |
| LINE |
| ------------------------------------------------------------------------------ |
| PFD1 the PFD output if the DMC drives the CAPT PFD DU |
| PFD2 the PFD output if the DMC drives the F/O PFD DU |
| ND1 the ND CAPT output if the DMC drives the CAPT ND DU |
| ND2 the ND F/O output if the DMC drives the F/O ND DU |
| EWD1 the EWD output if the DMC drives the EW DU |
| EWD2 the EWD output if the DMC(ECAM) drives the ND (capt or f/o) |
| SD1 the SD output if the DMC drives the SD |
| SD2 the SD output if the DMC(ECAM) drives the ND(capt or f/o) |
| together with EW DU invalid |
(6) Output busses
Two output buses are generated by the active DMCs, as follows:
Two output buses are generated by the active DMCs, as follows:
- one general high speed data bus
- one general low speed data bus
(7) The general high speed output bus of the Captain side is issued to control:
- the FWC1 and the FWC2
- the ECAM Control Panel
- the DMU
- the FDIU.
- the DFDR.
- the PVI (optional) or
- the HUD (optional)
(8) The general low speed output bus is issued to control:
- the CFDIU
This bus is not switched, and available on the three DMCs.
G. Weather Radar Buses (ARINC 453)
A Weather Radar equipment complying with ARINC 708-4 is installed.
Each DMC receives from the W/R transceiver unit his two data buses, D1 and D2.
The DMC processes information from the W/R transceiver provided that W/R operation is enabled by the W/R request control signal).
Provided that the W/R operation is requested on the W/R control unit, the ND presents a W/R image in all the ND modes except the PLAN mode. If both pilots select the PLAN mode, the DMCs send the W/R REQUEST discrete signal in the open state, which disables the W/R XCVR, thus avoiding useless operating hours.
Data bus selection:
Each DMC receives from the W/R transceivers units their two data buses, D1 and D2.
The DMC processes information from the operating W/R transceiver (only one at a time according to the position of the 1-2 selection switch on the W/R control unit and provided that W/R operation is enabled by the W/R request control signal).
Provided that the W/R operation is requested on the W/R control unit, the ND presents a W/R image in all the ND modes except the PLAN mode. If both pilots select the PLAN mode, the DMCs send the W/R REQUEST discrete signal in the open state, which disables the W/R XCVR, thus avoiding useless operating hours.
The DMCs which operate on side 1 normally work with the DATA 1 buses (XCVR 1-1 or XCVR 2-1), which correspond to the CAPT range selection.
However, the DMCs which operate on side 1 may operate with a DATA 2 bus, i.e. using the data corresponding to the range selected by the F/O, in case of an FMGC 1 failure which leads to an automatic changeover to the FMGC 2 data in the DMC 1.
In this case, the DMC 1 (or DMC 3 if the EIS DMC selector switch is set to CAPT/3) processes the DATA 2 bus from the W/R XCVR in operation.
The range markers and the mode on the Captain ND are then those corresponding to the F/O selection, which is indicated on the Captain ND by an amber message : SELECT OFFSIDE RANGE & MODE. This message may disappear sooner, if the Captain selects the same range as the First Officer. The same applies for the DMCs working on side 2, which normally use the D2 buses, but which use the D1 buses in case of FMGC 2 failure.
A Weather Radar equipment complying with ARINC 708-4 is installed.
Each DMC receives from the W/R transceiver unit his two data buses, D1 and D2.
The DMC processes information from the W/R transceiver provided that W/R operation is enabled by the W/R request control signal).
Provided that the W/R operation is requested on the W/R control unit, the ND presents a W/R image in all the ND modes except the PLAN mode. If both pilots select the PLAN mode, the DMCs send the W/R REQUEST discrete signal in the open state, which disables the W/R XCVR, thus avoiding useless operating hours.
Data bus selection:
Each DMC receives from the W/R transceivers units their two data buses, D1 and D2.
The DMC processes information from the operating W/R transceiver (only one at a time according to the position of the 1-2 selection switch on the W/R control unit and provided that W/R operation is enabled by the W/R request control signal).
Provided that the W/R operation is requested on the W/R control unit, the ND presents a W/R image in all the ND modes except the PLAN mode. If both pilots select the PLAN mode, the DMCs send the W/R REQUEST discrete signal in the open state, which disables the W/R XCVR, thus avoiding useless operating hours.
The DMCs which operate on side 1 normally work with the DATA 1 buses (XCVR 1-1 or XCVR 2-1), which correspond to the CAPT range selection.
However, the DMCs which operate on side 1 may operate with a DATA 2 bus, i.e. using the data corresponding to the range selected by the F/O, in case of an FMGC 1 failure which leads to an automatic changeover to the FMGC 2 data in the DMC 1.
In this case, the DMC 1 (or DMC 3 if the EIS DMC selector switch is set to CAPT/3) processes the DATA 2 bus from the W/R XCVR in operation.
The range markers and the mode on the Captain ND are then those corresponding to the F/O selection, which is indicated on the Captain ND by an amber message : SELECT OFFSIDE RANGE & MODE. This message may disappear sooner, if the Captain selects the same range as the First Officer. The same applies for the DMCs working on side 2, which normally use the D2 buses, but which use the D1 buses in case of FMGC 2 failure.
NOTE: The W/R equipment has identical D1 and D2 buses, each conveying all the data associated to both CAPT and F/O ranges.
NOTE: If there is a discrepancy between the range selection from the FCU and the range selection sent on the corresponding W/R data bus, no W/R image is displayed and the W/R RANGE red message is displayed.