(2)
Level flight or too shallow climb towards rising terrain (Mode 2).
(3)
Takeoff altitude loss (Mode 3).
(4)
Unsafe terrain clearance (Mode 4).
(5)
Excessive deviation below the glide slope (Mode 5).
(6)
Descent below decision height (DH) (Mode 6) (not used).
B. The GPWS consists of a ground proximity computer; two warning lights labeled PULL UP; a warning speaker; two glide slope warning indicator/inhibit switches labeled BELOW G/S; a ground proximity warning control module consists of a SYS TEST switch; a guarded flap/gear INHIBIT switch; and a GPWS failure monitor INOP light. Equipment location is shown in Fig. 1.
C. Primary power for the system is 115 volts ac supplied from the essential radio bus in panel P18 through a circuit breaker labeled GND PROXIMITY WARN. The warning indicator lights receives 28 volts dc power from the master dim and test system (Ref Chapter 33).
D. 26 volts ac is also received from the central air data system as a
reference voltage for the altitude rate circuits.Ground Proximity Warning Computer
_________________________________
A. The ground proximity warning computer (GPWC) is rack-mounted on shelf No. 4 of electronic equipment rack E2. The GPWC consists of a logic and power supply module, a comparator and closure warning, audio, voice, glide slope, monitor, and self-test modules. A power transformer and an interference capacitor are also mounted in the rear of the chassis above the electrical connector.
B. The computer receives glide slope deviation, barometric altitude rate, radio altitude, and gear and flap logic, from other airplane systems. The input signals are processed and signals are provided to warning devices if the airplane enters an unsafe flight path.
GPWS Warning Lights (Fig. 1)
___________________
A. A rectangular shaped red warning light labeled PULL UP is installed on the captain's and first officer's instrument panels. Access to the bulbs within the light assembly is provided by removing the lens cover.
B. The lights come on to provide a visual indication of mode 1, 2, 3, and 4 warnings.
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34-42-00
ú ú 03 Page 1 ú Jul 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FIRST OFFICER'S PANEL (P3)
OVERHEAD PANEL(P5)
. PULL UP WARNING LIGHT . BELOW G/S WARNING LIGHT/INHIBIT SWITCH . GPWS CONTROL PANEL
SEE
AND
CAPTAIN'S PANEL (P1) . PULL UP WARNING LIGHT . BELOW G/S WARNING
LIGHT/INHIBIT SWITCH
SEE
CENTER (P18)
SEE
A
R PULL UP
P-INHIBIT BELOW G/S A
Ground Proximity Warning System Component Location
Figure 1
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ú ú 05 Page 2 ú Jun 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
4. G/S Warning Lights (Fig. 1)
__________________
A. A rectangular shaped amber G/S (advisory) light labeled BELOW G/S is installed on the captain's and first officer's instrument panels. Access to the bulbs and a fuse within the light assembly is provided by removing the lens cover. The light comes on to provide a visual indication that the airplane is below the glide slope beam when an ILS frequency is selected.
B. The G/S warning light will inhibit the glide slope deviation warning when pressed, provided the hard glide slope warning is not already on.
5. Ground Proximity Warning System Control Module (Fig. 1)
______________________________________________
A. The ground proximity warning control module is located on the first officer's instrument panel. It consists of an amber INOP indicator light, a SYS TEST switch, and a guarded & lockwired flap/gear INHIBIT switch. The INOP indicator light comes on when the monitor circuit in the computer senses a fault condition. The TEST switch provides a confidence check of the system, either in flight or on ground. The flap/gear INHIBIT switch enables the pilots to simulate a flap down and a gear down condition when the switch is set to INHIBIT position. When placed in the INHIBIT position, the "TOO LOW-FLAPS" and "TOO LOW-GEAR" warnings are inhibited.
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