---------------------------------------------------------------------------
| Reported External Failures | |-------------------------------------------------------------------------| | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2)/GPWC (1WZ) | 1 | 34-41-33 | ---------------------------------------------------------------------------
**ON A/C ALL
C. BITE Implementation The BITE capability is implemented primarily in software. Most of the tests run continuously, while the remainder run only as the result of certain events (e.g. power-up). Failures are indicated by monitor output discretes, the ARINC 429 outputs, the Enhanced GPWC audio output, and on the MCDU (interactive mode). These failures are saved in the flight history memory if they occurred during flight. Some BITE failures inhibit alerts and warnings. In these cases, the self-test is inhibited. Internal test processing:
------------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | |----------------------------------------------------------------------------| | MCDU system | - CPU | 30 s | Relevant MCDU | | test | - RAM | | menu line key | | | - EPROM | | selection | | | - Wait state | | | | | - Non Envelope modulation NVM | | | | | - Watchdog timer | | | | | - A/D converter | | | | | - Voice generator | | | | | - ARINC 429 transmitter | | | | | - Software configuration data | | | | | base monitor | | | | | - ARINC 429 parity | | | | | - Software operating system | | | | | monitor | | | | | - Software watchdog monitor | | | | | - Envelope modulation NVM | | | | | - ARINC 429 receiver | | |
1EFF : ALL 1 34-48-00Page A96 1 1 Config-1 Aug 01/05 1 1 1CES 1 ------------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | |----------------------------------------------------------------------------| |----------------------------------------------------------------------------| | Cockpit | Ref. para. 8. A. | | Ref. para. 8. A.| | Self-test | | | | ------------------------------------------------------------------------------
R **ON A/C 061-099, 105-149, 151-199, 201-299, 301-399, 401-499,
D. Power-up Test Initialization and Cockpit Repercussions
(1)
Conditions of power-up test initialization
-How long the computer must be de-energized: 1 s.
-A/C configuration:
-whatever the A/C configuration on ground
(2)
Progress of power-up tests
-Duration: 20 s.
-Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded):
-none
(3)
Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed).
-
Tests pass:
-none
-
Tests failed:
-GPWS panel:
FAULT legend of SYS pushbutton switch on and/or
FAULT legend of pushbutton switch on
(depending on the faulty part)
-MASTER CAUT light on and single chime
-
ECAM warning:
NAV GPWS FAULT and/or
NAV GPWS TERR FAULT
(depending on the faulty part)
-
ECAM STATUS:
GPWS INOP and/or
GPWS TERR INOP
(depending on the faulty part)
1EFF : ALL 1 34-48-00Page A97 1 1 Config-1 Aug 01/05 1 1 1CES 1
GROUND PROXIMITY WARNING SYSTEM (GPWS) - DESCRIPTION AND OPERATION
__________________________________________________________________
1.
General
_______ (Ref. Fig. 001) The Ground Proximity Warning System (GPWS) generates aural and visual warnings if the aircraft adopts a potentially hazardous condition with respect to: Mode 1 - Excessive rate of descent Mode 2 - Excessive closure rate with terrain Mode 3 - Descent after takeoff and minimum terrain clearance Mode 4 - Unsafe terrain clearance Mode 5 - Descent below glide slope. The system is operative between 30 ft. and 2450 ft. radio altitude. Four pushbutton switches on the overhead panel enable the flight crew to inhibit an abnormal flap condition signal, all GPWS warning signals and a glide slope warning signal. A GPWS/G/S pushbutton switch located on the main instrument panel (Captain and F/O) is also used to initiate the GPWC self-test when the aircraft is above 1000 ft. or below 30 ft. radio altitude. The Ground Proximity Warning Computer (GPWC) is installed in the avionics compartment. Aural warnings are broadcast from the cockpit loud speakers. The FAULT legend of the SYS pushbutton switch, located on the overhead panel 21VU, comes on to indicate system fault. (Ref. Fig. 001) 中國(guó)航空網(wǎng) www.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 NAVIGATION 導(dǎo)航4(52)
