DOC AIRBUS | AMM A320FEIS - CONTROL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
This document defines EIS power supply in normal and emergency configurations and also EIS controls which are at the crew's disposal.
** ON A/C NOT FOR ALL This document defines EIS power supply in normal and emergency configurations and also EIS controls which are at the crew's disposal.
2. EIS Component Location
In emergency configuration, AC and DC power supply is restored for a few components, by means of the hydraulically driven Emergency generator. The hydraulic power source is the Ram Air Turbine (RAT).
In this configuration, the following FWS and EIS components are supplied:
** ON A/C NOT FOR ALL 
EIS - Component Location in the Cockpit - Sheet 1/2| FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | ATA REF |
|---|---|---|---|---|---|
| ** ON A/C ALL | |||||
| 1WT1 | DMC-1 | 85VU | 127 | 31-63-34 | |
| 1WT2 | DMC-2 | 86VU | 128 | 31-63-34 | |
| 1WT3 | DMC-3 | 85VU | 127 | 31-63-34 | |
| 2WT1 | PFD-CAPT | 3VU | 211 | 31-63-22 | |
| 2WT2 | PFD-F/O | 5VU | 212 | 31-63-22 | |
| 3WT1 | ND-CAPT | 3VU | 211 | 31-63-22 | |
| 3WT2 | ND-F/O | 5VU | 212 | 31-63-22 | |
| 4WT1 | DU-ECAM, UPPER | 4VU | 210 | 31-63-22 | |
| 4WT2 | DU-ECAM, LOWER | 4VU | 210 | 31-63-22 | |
| 6WT | CTL PNL-ECAM | 11VU | 210 | 31-61-12 | |
| 7WT1 | POT-PFD, CAPT | 301VU | 211 | 31-61-00 | |
| 7WT2 | POT-PFD, F/O | 500VU | 212 | 31-61-00 | |
| 8WT1 | POT-ND, CAPT | 301VU | 211 | 31-61-00 | |
| 8WT2 | POT-ND, F/O | 500VU | 212 | 31-61-00 | |
| 9WT1 | P/BSW-PFD/ND XFR, CAPT | 301VU | 211 | 31-61-00 | |
| 9WT2 | P/BSW-PFD/ND XFR, F/O | 500VU | 212 | 31-61-00 | |
| 18WT | SEL SW-EIS DMC | 8VU | 210 | 31-61-00 | |
| 19WT | SEL SW-ECAM/ND XFR | 8VU | 210 | 31-61-00 | |
| 25WT1 | P/BSW-CHRONO, CAPT | 131VU | 211 | 31-61-00 | |
| 25WT2 | P/BSW-CHRONO, F/O | 130VU | 212 | 31-61-00 | |
| 26WT | RELAY-BUS1 TO ESS BUS SWTG, DMC3 | 103VU | 126 | 31-61-00 | |
| ** ON A/C NOT FOR ALL | |||||
| 35WT | CCD CAPTAIN | 211 | 31-61-14 | ||
| 36WT | CCD FIRST OFFICER | 212 | 31-61-14 | ||
| ** ON A/C ALL | |||||
| 1WV1 | SDAC-1 | 85VU | 127 | 31-55-34 | |
| 1WV2 | SDAC-2 | 86VU | 128 | 31-55-34 | |
| 1WW1 | FWC-1 | 85VU | 127 | 31-53-34 | |
| 1WW2 | FWC-2 | 86VU | 128 | 31-53-34 | |
| 7WW | LOUD SPEAKER-CAPT | 831 | 211 | 31-53-21 | |
| 8WW | LOUD SPEAKER-F/O | 831 | 212 | 31-53-21 | |
| 15RN1 | POT-LOUD SPEAKER, CAPT | 301VU | 211 | 23-51-00 | |
| 15RN2 | POT-LOUD SPEAKER, F/O | 500VU | 212 | 23-51-00 | |
| ** ON A/C NOT FOR ALL | |||||
| 20WT1 | RELAY BOX-CAPT PFD-ND XFR | 301VU | 211 | 31-61-00 | |
| 20WT2 | RELAY BOX-F/O PFD-ND XFR | 500VU | 212 | 31-61-00 | |
| ** ON A/C NOT FOR ALL | |||||
| 20WT1 | RELAY BOX-CAPT PFD-ND XFR | 211 | 31-61-00 | ||
| 20WT2 | RELAY BOX-F/O PFD-ND XFR | 212 | 31-61-00 | ||
| ** ON A/C ALL | |||||
| 11WW1 | LT-MASTER CAUT, CAPT | 131VU | 211 | 31-52-00 | |
| 11WW2 | LT-MASTER CAUT, F/O | 130VU | 212 | 31-52-00 | |
| 13WW1 | WARN LT-AUTO LAND, CAPT | 131VU | 211 | 31-52-00 | |
| 13WW2 | WARN LT-AUTO LAND, F/O | 130VU | 212 | 31-52-00 | |
| 9WW1 | LT-MASTER WARN, CAPT | 131VU | 211 | 31-52-00 | |
| 9WW2 | LT-MASTER WARN, F/O | 130VU | 212 | 31-52-00 | |
In this configuration, the following FWS and EIS components are supplied:
- DMC1 (or DMC3 if selected by the Captain)
- CAPT PFD
- CAPT ND
- Upper ECAM DU
- FCU
- FWC1
- ECAM CTL PNL
- SDAC1.
NOTE: 1- * In emergency configuration, the ADIRU 3 is also supplied from the AC ESS BUS as soon as the ATT/HDG or the AIR DATA selector switch is set to CAPT/3.
2- The static inverter is used to supply the essential network for the few seconds following a real emergency configuration, due to the extension of the RAT and the time required to have the emergency generator nominal parameters.
During these few seconds, the CAPT ND is not supplied.
2- The static inverter is used to supply the essential network for the few seconds following a real emergency configuration, due to the extension of the RAT and the time required to have the emergency generator nominal parameters.
During these few seconds, the CAPT ND is not supplied.
3. EIS Controls
A. DU ON/OFF BRIGHTNESS Potentiometers
(1) EFIS DUs (PFD and ND)
By either side of the main instrument panel PFD and ND brightness controls are provided for each pilot.
By either side of the main instrument panel PFD and ND brightness controls are provided for each pilot.
(a) PFD
The PFD brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each PFD. This system provides adjustment of the DU symbology brightness in order to cope with the changes of the cockpit environmental lighting conditions. If it fails, manual control is retained.
When the potentiometer is set to the minimum (but not to OFF), the brightness of the display remains at a certain low threshold to show to the pilot that the DU is still in operation.
The extreme left position of the potentiometer switches off the PFD.
If a pilot switches off his PFD, the PFD image is automatically displayed on the adjacent display unit (the ND) instead of the ND image. In this case, the pilot can recover the ND image by means of the PFD/ND XFR pushbutton switch.
The PFD brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each PFD. This system provides adjustment of the DU symbology brightness in order to cope with the changes of the cockpit environmental lighting conditions. If it fails, manual control is retained.
When the potentiometer is set to the minimum (but not to OFF), the brightness of the display remains at a certain low threshold to show to the pilot that the DU is still in operation.
The extreme left position of the potentiometer switches off the PFD.
If a pilot switches off his PFD, the PFD image is automatically displayed on the adjacent display unit (the ND) instead of the ND image. In this case, the pilot can recover the ND image by means of the PFD/ND XFR pushbutton switch.
(b) ND
The ND brightness is manually controlled through a potentiometer made up of two concentric knobs:
To do this, the pilot have to use the PFD/ND XFR pushbutton switch.
As in the case of the PFD, these manual controls work in conjunction with the automatic brightness control system.
The ND brightness is manually controlled through a potentiometer made up of two concentric knobs:
- the outer knob enables a separate adjustment of the brightness of the weather radar image only.
- the inner knob enables adjustment of the general brightness of the ND symbology.
To do this, the pilot have to use the PFD/ND XFR pushbutton switch.
As in the case of the PFD, these manual controls work in conjunction with the automatic brightness control system.
(2) EFIS DUs (PFD and ND)
By either side of the main instrument panel PFD and ND brightness controls are provided for each pilot.
By either side of the main instrument panel PFD and ND brightness controls are provided for each pilot.
(a) PFD
The PFD brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each PFD. This system provides adjustment of the DU symbology brightness in order to cope with the changes of the cockpit environmental lighting conditions. If it fails, manual control is retained.
When the potentiometer is set to the minimum (but not to OFF), the brightness of the display remains at a certain low threshold to show to the pilot that the DU is still in operation.
The extreme left position of the potentiometer switches off the PFD.
If a pilot switches off his PFD, the PFD image is automatically displayed on the adjacent display unit (the ND) instead of the ND image. In this case, the pilot can recover the ND image by means of the PFD/ND XFR pushbutton switch.
The PFD brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each PFD. This system provides adjustment of the DU symbology brightness in order to cope with the changes of the cockpit environmental lighting conditions. If it fails, manual control is retained.
When the potentiometer is set to the minimum (but not to OFF), the brightness of the display remains at a certain low threshold to show to the pilot that the DU is still in operation.
The extreme left position of the potentiometer switches off the PFD.
If a pilot switches off his PFD, the PFD image is automatically displayed on the adjacent display unit (the ND) instead of the ND image. In this case, the pilot can recover the ND image by means of the PFD/ND XFR pushbutton switch.
(b) ND
The ND brightness is manually controlled through a potentiometer made up of two concentric knobs:
To do this, the pilot have to use the PFD/ND XFR pushbutton switch.
As in the case of the PFD, these manual controls work in conjunction with the automatic brightness control system.
The ND displays Onboard Airport Navigation System (OANS) information and is controlled with the Cursor Control Device (CCD) (for more data about the CCD, refer to Chapter 34-38-00).
The ND brightness is manually controlled through a potentiometer made up of two concentric knobs:
- the outer knob enables a separate adjustment of the brightness of the weather radar image only.
- the inner knob enables adjustment of the general brightness of the ND symbology.
To do this, the pilot have to use the PFD/ND XFR pushbutton switch.
As in the case of the PFD, these manual controls work in conjunction with the automatic brightness control system.
The ND displays Onboard Airport Navigation System (OANS) information and is controlled with the Cursor Control Device (CCD) (for more data about the CCD, refer to Chapter 34-38-00).
(3) ECAM DUs (ENGINE/WARNING and SYSTEM/STATUS)
ON/OFF and brightness controls are provided for each ECAM DU on the ECAM Control Panel.
For each DU, the brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each DU. If they fail, manual brightness control is retained.
The extreme left position of each potentiometer switches off the corresponding DU.
If the upper DU is switched off, the Engine/Warning image is automatically displayed on the lower ECAM DU.
ON/OFF and brightness controls are provided for each ECAM DU on the ECAM Control Panel.
For each DU, the brightness is manually controlled through a single potentiometer which works in conjunction with the automatic brightness control system provided by the light sensors located on the face of each DU. If they fail, manual brightness control is retained.
The extreme left position of each potentiometer switches off the corresponding DU.
If the upper DU is switched off, the Engine/Warning image is automatically displayed on the lower ECAM DU.
B. PFD/ND Transfer Manual Control
On either pilot instrument panel, a PFD/ND XFR pushbutton switch enables each pilot to cross-change the images between the PFD and ND.
At each action on this pushbutton switch, there is an inversion between the 2 images : the one which was displayed on the left DU is displayed on the right DU and vice-versa.
On either pilot instrument panel, a PFD/ND XFR pushbutton switch enables each pilot to cross-change the images between the PFD and ND.
At each action on this pushbutton switch, there is an inversion between the 2 images : the one which was displayed on the left DU is displayed on the right DU and vice-versa.
C. Transfer Selector Switches
Four transfer selector switches, mounted on the SWITCHING panel on the center pedestal, provide the crew with the following manual transfers
Four transfer selector switches, mounted on the SWITCHING panel on the center pedestal, provide the crew with the following manual transfers
- EIS DMC transfer, CAPT/3 or F/O/3, for EFIS and ECAM (DMC3 totally replaces DMC1 or DMC2 in case of failure of DMC1 or DMC2).
- ECAM/ND transfer, on the CAPT side or the F/O side (this transfer facility enables the crew to display an ECAM image to either ND, in case of failure of ECAM DUs).
- ADIRU source switching i.e. ADIRU 3 replacing ADIRU 1 or ADIRU 2 if they fail. Independent transfer means are provided for anemometric data (AIR DATA selector switch) and for attitude, heading and other inertial data (ATT HDG selector switch).
D. FCU-EFIS Control Sections
The EFIS control sections of the FCU, which are located either side of the FCU and are part of it, enable each pilot to select desired modes and data on his PFD and ND.
Both CAPT and F/O EFIS control sections are identical and give the same display possibilities on the CAPT and F/O PFD and ND.
Each EFIS control section and central auto flight control section features all the control and indication devices and can be removed separately.
Each EFIS control section of the FCU includes a PFD control part and a ND control part.
Briefly, an EFIS control section provides the following controls :
The EFIS control sections of the FCU, which are located either side of the FCU and are part of it, enable each pilot to select desired modes and data on his PFD and ND.
Both CAPT and F/O EFIS control sections are identical and give the same display possibilities on the CAPT and F/O PFD and ND.
Each EFIS control section and central auto flight control section features all the control and indication devices and can be removed separately.
Each EFIS control section of the FCU includes a PFD control part and a ND control part.
Briefly, an EFIS control section provides the following controls :
(1) PFD control part :
(Ref. Chap. 31-64-00)
(Ref. Chap. 31-64-00)
- Baro reference selector knob, for setting the STD altitude baro reference or the QNH baro reference.
- Display window for the baro correction reference value.
- hPa/inches of Hg selector knob (outer ring concentric with the baro reference selector knob).
- FD pushbutton switch (when illuminated white, the guidance orders, FD bars or FPD symbol are out of view).
- LS pushbutton switch (when illuminated green, the LS LOC and GLIDE scales and the LS data deviations, LS course, LS frequency/ identification are displayed).
(2) PFD control part :
(Ref. Chap. 31-64-00)
(Ref. Chap. 31-64-00)
- Baro reference selector knob, for setting the STD altitude baro reference, the QNH baro reference or the QFE baro reference.
- Display window for the baro correction reference value.
- hPa/inches of Hg selector knob (outer ring concentric with the baro reference selector knob).
- FD pushbutton switch (when illuminated white, the guidance orders, FD bars or FPD symbol are out of view).
- LS pushbutton switch (when illuminated green, the LS LOC and GLIDE scales and the LS data deviations, LS course, LS frequency/ identification are displayed).
(3) ND control part :
(Ref. Chap. 31-65-00)
(Ref. Chap. 31-65-00)
- ND mode selector switch
5 modes are available : ROSE-NAV, ROSE-LS, ROSE-VOR, ARC, PLAN and the WXR image can be obtained in all modes except the PLAN mode. - Scale selector switch
The following scales are available for the map and WXR images : 10, 20, 40, 80, 160, 320 NM. - ADF-OFF-VOR 1 and 2 selector switches for the display of the relevant data (bearing, station : identification/frequency).
- 5 pushbutton switches : CSTR (CONSTRAINT), WPT (WAYPOINT), VOR.D (VOR-DME), NDB (NON-DIRECTIONAL BEACON), ARPT (AIRPORT) when a given pushbutton switch is illuminated green (only one at a time), the corresponding data from the FMS data base is displayed on the ND.
NOTE: In case of total loss of the FCU, the DMCs automatically select some controls by default:
- for PFD :
STD baro reference
FD OFF
LS selected - for ND :
ROSE-NAV mode
80 NM
VOR 1
ADF 2
(4) ND control part :
(Ref. Chap. 31-65-00)
(Ref. Chap. 31-65-00)
- ND mode selector switch
5 modes are available : ROSE-NAV, ROSE-LS, ROSE-VOR, ARC, PLAN and the WXR image can be obtained in all modes except the PLAN mode. - Scale selector switch
The following scales are available for the map and WXR images : 10, 20, 40, 80, 160, 320 NM. - ADF-OFF-VOR 1 and 2 selector switches for the display of the relevant data (bearing, station : identification/frequency).
- 5 pushbutton switches : CSTR (CONSTRAINT), WPT (WAYPOINT), VOR.D (VOR-DME), NDB (NON-DIRECTIONAL BEACON), ARPT (AIRPORT) when a given pushbutton switch is illuminated green (only one at a time), the corresponding data from the FMS data base is displayed on the ND.
NOTE: In case of total loss of the FCU, the DMCs automatically select some controls by default:
- for PFD :
STD baro reference
FD OFF
LS selected - for ND :
ROSE-NAV mode
80 NM
VOR 1
ADF 2
(5) ND - CCD control part:
(Ref. Chap. 34-38-00)
(Ref. Chap. 34-38-00)
- The OANS is interfaced with the CAPT and the F/O CCDs through two dedicated RS-422 serial links.
- Conversely, when the OANS image is not displayed, the OANS inhibits CCD commands.
E. ECAM Control Panel
The ECAM Control Panel includes controls required for operation of the ECAM system, as regards the display of various messages (memo, warning, caution, procedures, status) and the display of the different A/C system pages (synoptic diagrams).
Briefly, it provides the following controls:
The ECAM Control Panel includes controls required for operation of the ECAM system, as regards the display of various messages (memo, warning, caution, procedures, status) and the display of the different A/C system pages (synoptic diagrams).
Briefly, it provides the following controls:
- upper and lower ECAM DU brightness-ON/OFF potentiometers (see Para. 4.A.).
- system keys for manual selection of the A/C system page.
- ALL key for the cyclic display of all the A/C system pages, at 1 second intervals approx., which enables the crew to choose a given page in case of failure of the above system keys (the page on display is that present when the ALL key is released).
- RCL key for recalling an alert which had been inhibited or suppressed.
- STS key for calling the STATUS page on the lower ECAM DU.
- 2 CLR keys which enable the crew to clear the warning/caution messages and to get automatically the A/C system pages in relation with the detected warnings or cautions.
- EMER CANC guarded key for cancelling any aural warning including GPWS ones.
F. Drawing the crew members attention
(1) By visual devices
A red MASTER WARN light and an amber MASTER CAUT light are installed on the glareshield in front of each pilot as attention getters to draw his attention to the ECAM DUs if a warning or a caution occurs. These lights are of the spring-loaded pushbutton switch type.
Each FWC controls both CAPT and F/O lights.
A red MASTER WARN light and an amber MASTER CAUT light are installed on the glareshield in front of each pilot as attention getters to draw his attention to the ECAM DUs if a warning or a caution occurs. These lights are of the spring-loaded pushbutton switch type.
Each FWC controls both CAPT and F/O lights.
(2) By aural devices
Two loudspeakers are installed in the cockpit, one in front of each pilot.
They provide the crew with general communication voices and sounds, GPWS aural warnings, automatic call-out synthetic voices, and at last warning and caution aural warnings.
The ON/OFF and volume control potentiometers can only control the general communication voices and sounds.
Two loudspeakers are installed in the cockpit, one in front of each pilot.
They provide the crew with general communication voices and sounds, GPWS aural warnings, automatic call-out synthetic voices, and at last warning and caution aural warnings.
The ON/OFF and volume control potentiometers can only control the general communication voices and sounds.
G. INT LT/ANN LT Switch
On the ground, when performing a cockpit light test (by means of the INT LT/ANN LT switch), all the DUs present fixed warning flag patterns, showing flags and annunciators at their proper location.
This mode is inhibited in flight.
The test is activated by the DMCS on reception of a ground discrete signal at their contact pin AB8F.
On the ground, when performing a cockpit light test (by means of the INT LT/ANN LT switch), all the DUs present fixed warning flag patterns, showing flags and annunciators at their proper location.
This mode is inhibited in flight.
The test is activated by the DMCS on reception of a ground discrete signal at their contact pin AB8F.