(a)  There exists within the GPWC software, built in test equipment or BITE. Much of this BITE is run continuously, while some tests are run only as the result of certain events (e.g. power up, self test, etc.). This BITE is capable of logging failure for the last 10 flights in non-volitile flight history memory storage for later recovery.
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A 737-300/400/500MAINTENANCE MANUAL

Ground Proximity Warning System Component Location
Figure 1 (Sheet 1)

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A 737-300/400/500MAINTENANCE MANUAL

GPWS CONTROL PANEL

BITE DISPLAY
STATUS/HISTORY SWITCH

GPWC 
PRESENT FLIGHT HISTORY 0 0 0 0 0 0 0 0 STATUS STATUS/HISTORY 

GROUND PROXIMITY WARNING COMPUTER

Ground Proximity Warning System Component Location
Figure 1 (Sheet 2)

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 2.
3.

4.

5.

A
737-300/400/500MAINTENANCE MANUAL
 C.  The GPWS consists of a ground proximity computer, two warning lights labeled PULL UP, two glide slope warning indicator/inhibit switches labeled BELOW G/S, a ground proximity warning control module which consists of a SYS TEST switch and a GPWS failure monitor INOP light. Equipment location is shown in Fig. 1.
 D.  AIRPLANES WITH SEPARATE FLAP AND GEAR INHIBIT SWITCHES; The GPWS has a guarded FLAP INHIBIT switch and a guarded GEAR INHIBIT switch.
 E.  Primary power for the system is 115 volts ac supplied from the essential radio bus in panel P18 through a circuit breaker labeled GND PROX WARN. The warning indicator lights receives 28 volts dc power from the master dim and test system (Ref Chapter 33).
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 seven assemblies: processor/memory, input/output, BITE display, FMC, power supply, harness and chassis.
 B.  The computer receives glide slope deviation, barometric altitude rate, radio altitude, gear and flap logic, airplane position and flight path acceleration information 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.WINDSHEAR Warning Lights
________________________
 A.  The visual indication of a windshear condition is provided on both the captain's and first officer's EADI. During windshear conditions, WINDSHEAR will be displayed in red on the EADI ball approximately 1/3 up from the bottom.
 B. The indication will be present as long as a windshear condition exists.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.
　
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