B. Pushbutton Switches
 (Ref. Fig. 001)
 The pushbutton switches are located on the overhead panel 21VU.

 (1)
 LDG FLAP 3 pushbutton switch 13WZ To avoid nuisance warnings during approach, the GPWC needs to know at which flap position the crew intends to land. The LDG FLAP 3 pushbutton switch (item 4), when pressed (in) (white ON legend on), indicates to the GPWC that the pilot intends to land in flap 3 position, inhibits the GPWC warnings ''TOO LOW FLAPS''. When released (out), the pushbutton switch indicates to the GPWS that the pilot intends to land in flap FULL position. The GPWS FLAP message is permamently displayed in green on the MEMO of the ECAM display unit if no warning is in progress.

 (2)
 FLAP MODE pushbutton switch 7WZ The pushbutton switch (item 3), when pressed (in) (white OFF legend on), overrides flap abnormal condition input.

 (3)
 SYS pushbutton switch 9WZ The pushbutton switch (item 1), when pressed (in) (white OFF legend on), inhibits all the GPWS warnings.

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 (4) G/S MODE pushbutton switch 11WZ The pushbutton switch (item 2), when pressed (in) (white OFF legend on), inhibits the glide slope mode.
 C. SYS Pushbutton Switch 9WZ
 (Ref. Fig. 001)

 (1)
 The SYS pushbutton switch, located on the overhead panel 24VU, provides a FAULT warning indicating that a system fault has been detected by the GPWC.

 (2)
 When the FAULT legend comes on, all the ground proximity warnings are inhibited and no GPWC self-test is possible.

 (3)
 When the FAULT legend comes on, messages are displayed on the upper ECAM display unit (if they are not inhibited by the FWC): NAV:

 -
GPWS FAULT (amber) associated with action requested

 -
GPWS OFF (cyan).
 A fault message is sent to the CFDIU.
 A GPWS message (amber) is also displayed on the STATUS page on the
 lower ECAM display unit.

 6. Operation
_________
 A. General
 (1) Warning modes The serial digital data and discrete data inputs are interfaced and used in different combinations to monitor aircraft vertical performance. The following functions are monitored: Mode 1 - Excessive rate of descent (Ref. Fig. 007) Mode 2 - Excessive closure rate with terrain (Ref. Fig. 008) Mode 3 - Descent after takeoff and minimum terrain clearance (Ref. Fig. 009) Mode 4 - Unsafe terrain clearance (Ref. Fig. 010) Mode 5 - Descent below glide slope (Ref. Fig. 011)
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 Excessive Rate of Descent
 Figure 007

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 Terrain Cloture Rate - Mode
 Figure 008

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 Descent After Takeoff
 Figure 009

R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 21 1 1 Config-2 May 01/05 1 1 1CES 1

 Unsafe Terrain Clearance
 Figure 010

R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 22 1 1 Config-2 May 01/05 1 1 1CES 1

 Descent Below Glide Slope
 Figure 011

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 (2) Warning messages (Ref. Fig. 008, 009, 010, 011) Each mode computes and compares aircraft behaviour with a corresponding warning envelope. If the warning envelope is penetrated, visual and aural warnings are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows:
 MODE  AURAL WARNING  VISUAL WARNING
 1  SINK RATE  GPWS
 1  WHOOP WHOOP PULL UP  GPWS
 2  TERRAIN  GPWS
 2  WHOOP WHOOP PULL UP  GPWS
 3  DON'T SINK  GPWS
 3  TERRAIN  GPWS
 4  TOO LOW TERRAIN  GPWS
 4  TOO LOW GEAR  GPWS
 4  TOO LOW FLAPS  GPWS
 5  GLIDE SLOPE  G/S

 Each of these warnings inhibits the automatic call out.
 NOTE : During mode 2, the TERRAIN warning is broadcast for 1.4
____ seconds and then, unless the warning envelope is departed, changes to WHOOP WHOOP PULL UP. This latter warning will be continuously broadcast until the aircraft departs from the original warning envelope, then the TERRAIN warning is broadcast again until the aircraft has climbed through a further 300 ft. of radio altitude.
 (3) Inhibitions Warnings may be cancelled by:
　
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