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 6.  Warning Speaker
_______________
 A.  A warning speaker is installed in overhead panel P5. The speaker provides an aural indication that the GPWC has generated a warning of an unsafe flight path.
 7.  Operation (Fig. 2 & 3)
_________
 A.  The GPWS is operational when load control center P18 is energized and the GPWS, CADC, VHF-NAV, and LRRA circuit breakers are closed.
 B.  Signal inputs to the GPWC consist of radio altitude information from LRRA No. 1, mach and altitude rate information from central air data computer No. 1, and glide slope deviation from the VHF NAV system.
 (1)  
The LRRA system provides the GPWS with radio altitude, and an altitude trip when the airplane descends below the decision height (mode 6, when activated) set on the captain's radio altitude indicator. LRRA signals are used in the control of all modes. Mode 2 requires a radio altitude rate signal (terrain closure rate) which is derived by the computer, from the radio altitude signal. The radio altitude signal is a dc voltage which is a function of airplane height above ground level and is useful to approximately 2500 feet.

 (2)  
The CADC system provides mach and barometric altitude rate signals to the GPWS computer. Altitude rate is used for the computations of mode 1 conditions, and is used to derive altitude loss, used in the computation of mode 3 conditions. The barometric rate signal is ac with a scale of 250 mv/1000 fpm altitude change. This rate signal is in phase with the 26-volt ac reference from the CADC during ascent and out-of-phase during descent. The mach signal is used to set warning thresholds for mode 2 and mode 4 computations. It is a three wire synchro output calibrated from zero degrees for 0.2 mach indication and increasing to one synchro revolution for a 1.2 mach indication.

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 34-42-00
 ú ú 04 Page 3 ú Jun 25/86

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

FLAP POSITION
GEAR DOWN

SYS TEST
GROUND PROXIMITY TEST SWITCH
VALID ALTITUDE
LRRA R/T UNIT
ILS DC
GLIDE SLOPE/ S FLAG
GLIDE SLOPE DEVIATION
VHF NAVIGATION SYSTEM

FLAP/GEAR
POSITION VALIDITY MONITOR
TEST AUDIBLE WARNING
ALTITUDE/
TRIPS
NAV
INPUTS

GROUND PROXIMITY COMPUTER

SAME AS
CAPTAIN'S

FIRST OFFICER'S WARNING LIGHTS AND INHIBIT SWITCH
INOP
FAILURE MONITOR LIGHT
GROUND PROXIMITY WARNING SPEAKER

Ground Proximity Warning System Block Diagram
Figure 2 (Sheet 1)

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 34-42-00

 INHIBIT SWITCH  ú
 ú  02  Page 4
 ú  Mar 15/95 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
115V AC

VALID MACH ALT RATE AIR DATA COMPUTER 
 

FLAP POSITION 
 

GEAR DOWN 
 

 

SYS TEST GROUND PROXIMITY TEST SWITCH 
VALID 
 
ALTITUDE 
LRRA R/T UNIT ILS DC S FLAG GLIDE SLOPE/ GLIDE SLOPE 
 

DEVIATION
VHF NAVIGATION SYSTEM
A 737-300/400/500MAINTENANCE MANUAL

POWER IN
WARN MODES 1,2,3 AND 4

GLIDE SLOPE

WARN

ADVISORY
(MODE 5)

INHIBIT

ADC INPUT
FLAP POSITION
GEAR POSITION
VALIDITY MONITOR
TEST AUDIBLE WARNING

ALTITUDE/ TRIPS
NAV INPUTS

GROUND PROXIMITY COMPUTER
Ground Proximity Warning System Block Diagram
Figure 2 (Sheet 2)

 

CAPTAIN'S WARNING LIGHTS AND INHIBIT SWITCH
SAME AS
CAPTAIN'S

FIRST OFFICER'S WARNING LIGHTS AND INHIBIT SWITCH
INOP
FAILURE MONITOR LIGHT
GROUND PROXIMITY WARNING SPEAKER

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