(5) GPWS/TERR pushbutton switch 31WZ
-When this pushbutton switch (item 1) is pressed (white OFF legend on), the TAD and TCF functions are inhibited (visual display and audio inhibition).
-The pushbutton switch provides a FAULT warning indicating that a failure of TAD and/or TCF functions has been detected by the Enhanced GPWC. When the FAULT legend comes on, the following messages are displayed: . on the upper ECAM display unit if they are not inhibited by the FWC:
NAV - GPWS TERR DET FAULT (amber)
GPWS TERR.............OFF (cyan) . in the INOP SYS item, on the STATUS page of the lower ECAM display unit:
GPWS TERR (amber)
A fault message is sent to the CFDIU.
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(6)
CAPT and F/O GPWS/G/S pushbutton switches 5WZ and 4WZ These pushbutton switches, located on panels 301VU and 500VU, have two functions when pressed (in):
-
they cancel the glide slope alert, or
-
they initiate the self-test sequence if the aircraft is on ground.
(7)
CAPT and F/O TERR ON ND pushbutton switches 30WZ1 and 30WZ2 These pushbutton switches (items 6 and 7) allow the crew to select or deselect terrain display on ND. The ON legends indicate that terrain data is displayed on ND (following manual or automatic pop up selection).
**ON A/C ALL
7. Operation
_________
**ON A/C 106-149, 215-299, 301-399,
A. General
(1)
Warning modes The serial digital data and discrete data inputs are interfaced and used in different combinations to monitor aircraft situation awareness with respect to the terrain. The following functions are implemented within the Enhanced GPWS: 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 Terrain Awareness and Display (TAD) Terrain Clearance Floor (TCF)
(2)
Aural alert messages Each mode computes and compares aircraft behaviour with a corresponding alert envelope. If the alert envelope is penetrated, visual and aural alerts are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows:
R 1EFF : ALL 1 34-48-00Page 73 1 1 Config-1 Aug 01/05 1 1 1CES 1 Each of these alerts inhibits the automatic call out.
MODE AURAL ALERTS VISUAL ALERTS
1 SINK RATE GPWS
1 PULL UP PULL UP
2 TERRAIN GPWS
2 TERRAIN TERRAIN PULL UP
2 PULL UP PULL UP
3 DON'T SINK DON'T SINK GPWS
4 TOO LOW TERRAIN GPWS
4 TOO LOW GEAR GPWS
4 TOO LOW FLAPS GPWS
5 GLIDE SLOPE GPWS
TAD TERRAIN AHEAD GPWS
TAD TERRAIN AHEAD PULL UP PULL UP
TCF TOO LOW TERRAIN GPWS
(3)
Inhibitions (Ref. Fig. 009) Alerts may be cancelled by:
(a)
Pressing the EMER CANC key on the ECAM control panel (aural alert only).
(b)
Pressing the PULL UP/GPWS pushbutton switch on the main instrument panel for Mode 5 (glide slope) visual and aural alert. This inhibition is temporary and the mode is automatically reactivated for a new envelope penetration.
(c)
Pressing the G/S MODE pushbutton switch on the overhead panel for Mode 5 (glide slope) visual and aural alert (permanent inhibition).
(d)
Pressing the SYS pushbutton switch on the overhead panel for inhibition of GPWS Modes 1 to 5 (visual and aural alerts).
(e)
Pressing the TERR pushbutton switch on the overhead panel for inhibition of TAD and TCF functions (visual and aural alerts).
(f)
All aural messages are inhibited if a stall or a windshear (if WR/PWS is installed) is in progress.
(4)
Faults which prevent normal Enhanced GPWC operation are stored in the BITE memory. They can be read on the MCDU.
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R **ON A/C 401-499,
R A. General
R (1) Warning modes
R The serial digital data and discrete data inputs are interfaced and
R used in different combinations to monitor aircraft situation
R awareness with respect to the terrain. The following functions are
R implemented within the Enhanced GPWS:
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