EIS - Component Location in the Cockpit - Sheet 1/2
 Figure 001

 1EFF : ALL 1 31-61-00Page 3/4 1 1 Feb 01/98 1 1 1CES
1

 EIS - Component Location in the Cockpit - Sheet 2/2
 Figure 002

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 31-61-00Page 5/6 1201-299, 301-302, 1May 01/05 1 1 1CES

 EIS - Component Location in the Avionics Compartment
 Figure 003

R 1EFF : 106-149, 303-399, 401-499, 1 31-61-00Page 7 1 1 Aug 01/05 1 1 1CES 1

 EIS - Component Location in the Avionics Compartment
 Figure 004

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 31-61-00Page 8 1201-299, 301-302, 1May 01/05 1 1 1CES 1

 EIS - Location of CAPT and F/O PFD-ND XFR Relay Boxes R Figure 005
 1EFF : ALL 1 31-61-00Page 9 1 1 Feb 01/05 1 1 1CES 1 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:

 -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.
 1EFF : ALL 1 31-61-00Page 10 1 1 Feb 01/05R 1 1 1CES 1

 3. EIS Controls
____________
 A. DU ON/OFF BRIGHTNESS Potentiometers R (Ref. Fig. 006)
 (1) EFIS DUs (PFD and ND) 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.

 (b)
 ND 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. The extreme left position of the inner knob switches off the ND. In this case, the ND image is not automatically displayed on the PFD. 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.
 1EFF : ALL 1 31-61-00Page 11 1 1 Feb 01/05 1 1 1CES 1

 Wiring Diagram Between DUs and Brightness ON/OFF Potentiometers R Figure 006
 1EFF : ALL 1 31-61-00Page 12 1 1 Feb 01/05 1 1 1CES 1

 (2) 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.
 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.
 C. Transfer Selector Switches
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM 指示/記錄系統(tǒng) 7(97)