SD - HYD Page
 Figure 031 
R 1EFF :  401-499,  1  31-60-00 Page 72 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 SD - BLEED Page
 Figure 032 
R 1EFF :  401-499,  1  31-60-00 Page 73 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 SD - WHEEL Page
 Figure 033 
R 1EFF :  401-499,  1  31-60-00 Page 74 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 The APU Page
 (Ref. Fig. 034)
 Item 1: APU electrical generator: load/voltage/frequency
 Item 2: APU AVAILABLE message
 Item 3: APU bleed valve and pressure
 Item 4: APU FUEL low pressure message
 Item 5: APU air intake flap message
 Item 6: APU low oil level message
 Item 7: APU exhaust gas temperature indication
 Item 8: APU EGT amber line
 Item 9: APU speed N indication
 Item 10: N amber line
 The DOOR/OXY Page
 (Ref. Fig. 035)
 Item 1: Cockpit oxygen indication
 Item 2: Door status
 Item 3: Door escape slide indication
 Item 4: Airstairs door (option)
 Item 5: Cargo door
 Item 6: Bulk cargo door (option)
 All the SD pages present in the lower part of the symbology, a
 specific area used to permanently display various parameters
 such as TAT, SAT, UTC,...
 (Ref. Fig. 036)

 The CRUISE page:
 This page gathers the main system parameters to be monitored
 by the crew during the cruise. The CRUISE Page
 (Ref. Fig. 037)
 Item 1: Oil quantity per engine
 Item 2: Fuel used indication per engine
 Item 3: Engine vibration indication
 Item 4: Landing elevation indication
 Item 5: Cabin vertical speed indication
 Item 6: Cabin altitude indication
 Item 7: Cargo temperature indication
 Item 8: Cabin temperature indication

 The STATUS page:
 This special page called STATUS page provides the crew with an
 operational summary of aircraft condition.
 This page is presented either automatically once the crew has
 cleared all the SD aircraft system pages which correspond to
 the current warning/caution or, manually using the STS key
 located on the ECAM control panel.
 (Ref. Fig. 038)

R 1EFF : 401-499, 1 31-60-00Page 75 1 1 Config-2 Aug 01/05 1 1 1CES 1

 SD - APU Page
 Figure 034 
R 1EFF :  401-499,  1  31-60-00 Page 76 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 INTENTIONALLY BLANK

R 1 1

31-60-00Page 77
1 1 Config-2 May 01/05 1 1 1CES 1 SD - DOOR/OXY Page Figure 035 (SHEET 1)

R 1EFF : 401-499, 1 31-60-00Page 78 1 1 Config-2 Aug 01/05 1 1 1CES 1 SD - DOOR/OXY Page Figure 035 (SHEET 2)

R 1EFF : 401-499, 1 31-60-00Page 79 1 1 Config-2 Aug 01/05 1 1 1CES 1

 SD - Permanent Data
 Figure 036 
R 1EFF :  401-499,  1  31-60-00 Page 80 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 SD - CRUISE Page
 Figure 037 
R 1EFF :  401-499,  1  31-60-00 Page 81 
1  1  Config-2 Aug 01/05
 1  1
 1CES  1

 Lower ECAM - STATUS Page
 Figure 038

R 1EFF : 401-499, 1 31-60-00Page 82 1 1 Config-2 Aug 01/05 1 1 1CES 1 F. General Messages

 (1)
 INVALID DISPLAY UNIT The Display Unit is initialized by a power on self test. When this test fails the message: INVALID DISPLAY UNIT is displayed in the central area of the related Display Unit.

 (2)
 INVALID DATA When the DMC is not able to send the data to the DU, the message INVALID DATA is displayed in the central part of the related DU.

 6. BITE and Test
_____________
 A. General The EIS computers include a self-test function i.e. a Built-In Test Equipment (BITE) and are connected to the CFDS maintenance bus for centralization of the whole maintenance data. Each CFDIU carries out the BITE functions at once for itself and for its connected DUs. The BITE detects internal failures/input parameters failure, minimizes undetected failures and facilitates the maintenance. The events such as anomaly, abnormal disengagement or failure are dated, coded and stored in Non-Volatile Memories (NVM) (BITE memory). This recording is capable of several flights. Each DMC is connected to the unique CFDIU maintenance bus which sends dating information (GMT, flight number, date,...) and control words related to the test functions in return. In case of detected failure, each DMC sends immediately to the CFDIU a message in plain English which states the failure and the concerned LRU. In addition, the DMCs are addressed directly by the CFDIU in order to perform detailed trouble shooting using direct access to component BITE memories. In this mode, available in ground only, the DMCs transmit to the CFDIU their detailed BITE memory contents, according to the CFDIU requests. (For further details, Ref. to 31-69-00).
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 指示/記錄系統 7(42)