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altitude is greater than 700 feet.
XA (e) Glide slope deviation warning (mode 5) (AT ALL; LH ALL)
1) A soft glide slope warning is provided if the deviation of
the airplane below the glide slope exceeds 1.3 dots when
the airplane is between 1000 and 150 feet of radio
altitude. A hard warning is provided if the deviation of
the airplane below the glide slope exceeds 2 dots when
the airplane is between 300 and 150 feet of radio
altitude.
2) In order to allow the pilot to purposely descend below
the glide slope without triggering a warning, the glide
XA slope warning mode may be inhibited by pressing the PUSH
XA TO INHIBIT switch when the radio altitude is below 1000
feet and the hard warning is not in progress. The glide
slope warning cannot be inhibited when the hard warning
is on.
XA (f) Glide slope deviation (mode 5) (AF ALL; GN ALL; MD ALL;
XA VM ALL)
1) A glide slope warning is provided if the deviation of
airplane below the glide slope exceeds 1.3 dots when the
airplane is between 1000 and 150 feet of radio altitude.
The repetition rate of voice warning is increased as the
deviation below the glide slope beam increases.
2) In order to allow the pilot to purposely descend below
the glide slope without triggering a warning, the glide
XA slope warning mode may be inhibited by pressing the PUSH
XA TO INHIBIT switch when the radio altitude is below 1000
feet. Ascent to a radio altitude of above 1000 feet will
enable the below glide slope warning, if it has been
cancelled.
(5) The GPWC warning outputs consist of the following:
(a) A variable 400- to 800-Hz tone followed by a voice warning
PULL UP broadcast over the cockpit interphone speakers.
(b) Ground warning illuminates the red PULL UP or GPWS warning
light on the pilot's lightshield.
(6) The glide slope deviation warning outputs provide a voice alert
GLIDE SLOPE broadcast over the warning speaker and illuminate the
amber BELOW G/S warning indicator light on the pilots' windshield.
(7) The ground proximity warning output for all modes is inhibited
whenever the stall warning system is activated. (On GN and AF
airplanes incorporating SB 34-2171, inhibiting of ground proximity
warning during stall warning is eliminated.) The warning outputs
are also recorded through the flight recorder system.
EFFECTIVITY
AF ALL;LH ALL;SN ALL; CONFIG 1 AT ALL;GN ALL;MD ALL; 01 Page 17 VM ALL Dec 25/87
34-46-00
(8) System self-test may be initiated by pressing the GROUND PROXIMITY
TEST switch. During self-test, the GPWS, BELOW G/S, and GPWS INOP
indicators come on, and a loud GLIDE SLOPE and WHOOP WHOOP PULL UP
aural warning occurs. The PULL UP aural warning may repeat up to
seven times.
NOTE: On LH ALL,____
the GLIDE SLOPE aural warning comes on at a reduced volume.
XA (9) On AT ALL,
self-test may also be initiated by pressing the test switch in
front of the computer. In addition to the aural and visual
warnings at a reduced level occurring as described above, the fault
indicator lamps on the computer come on flashing momentarily
indicating signals are valid, and the mode annunciators on the
computer will display white as each mode is exercised and checked.
The GPWC OK light comes on momentarily when all modes are valid.
The annunciator may be reset manually by means of the RESET switch
on the computer or automatically when radio altitude is greater
than 50 feet.
XA (10) On LH ALL,
self-test may also be initiated by pressing the test switch in
front of the computer. In addition to the aural and visual
warnings at a reduced level occurring as described above, the fault
indicator lamps on the computer come on flashing momentarily
indicating signals are valid. The GPWC OK light comes on
momentarily when all modes are valid.
XA (11) On AF ALL; GN ALL; MD ALL; VM ALL;
self-test may also be initiated by pressing the test switch on the
front of the computer. In addition to the aural and visual
warnings in the cockpit, the validity indicators will illuminate
on the computer for the modes that are operationally valid. The
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