(r)  
Put the landing gear selector to DOWN.

 S 725-101
 (7)  Do a Test of the Glide Slope Deviation - Mode 5 as follows:
 (a)  Set a course on the captain's autopilot mode control panel to the airplane heading.
 NOTE: Glide slope warning will be inhibited if course and
____ airplane heading have a difference of greater than 90 degrees.
 (b)  
AIRPLANES WITH A SINGLE FLAP/GEAR INHIBIT SWITCH; Put the FLAP/GEAR INHIBIT switch in the NORMAL position.

 (c)  
AIRPLANES WITH SEPARATE FLAP AND GEAR INHIBIT SWITCHES; Put the FLAP INHIBIT and GEAR INHIBIT switches in the NORMAL position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.
 AIRPLANES WITH -201 THRU -203,  ú 34-42-01
 -205 OR -206 GPWC  ú ú 10 Page 506 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (d)  
Tune the VHF NAV-1 receiver to a localizer test frequency.

 (e)  
Using the VOR/ILS-1, supply a zero deviation glide slope test signal.

 (f)  
Use the VOR/ILS-1 to supply a larger than 2 dots up deviation glide slope test signal. 1) Make sure the Captain's and the First Officer's BELOW G/S

 lights come on and a soft aural GLIDESLOPE warning is heard.

 (g)  
Decrease radio altitude to 200 feet.

 1)  Make sure the Captain's and the First Officer's BELOW G/S lights are on and a louder more frequent aural GLIDESLOPE warning is heard.

 (h)  
Put the LIGHTS test switch to DIM position.

 1)  Make sure the Captain's and the First Officer's BELOW G/S lights dim and aural GLIDESLOPE warning continues.

 (i)  
Put the LIGHTS switch to the BRT position.

 (j)  
Push the Captain's BELOW G/S light.
 1) Make sure all warnings stop.

 (k)  
Increase radio altitude to 1500 feet.

 (l)  
Decrease radio altitude to 500 feet.

 1)  Make sure that the Captain's and First Officer's BELOW G/S lights come and and aural GLIDESLOPE warning is heard.

 (m)  
Push the First Officer's BELOW G/S light.
 1) Make sure all warnings stop.

 G.  Put the Airplane Back to Its Usual Condition
 S 865-109
 (1)  
Slowly remove all pitot-static pressures.

 (2)  
Remove the test equipment.

 (3)  
Remove electrical power if it is not necessary (Ref 24-22-00/201).

 S 085-110
 S 865-006
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.
 AIRPLANES WITH -201 THRU -203,  ú 34-42-01
 -205 OR -206 GPWC  ú ú 08 Page 507 ú Jul 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST
_________________________________________________
 1.  General_______
 A.  This subject has two tasks. One task is an operational test and the other a system test. The operational test is the self-test mode of the Ground Proximity Warning Computer (GPWC). The system test uses the maintenance label (hex code) to do a complete check of the GPWS.
 TASK 34-42-02-715-001
 2.  Ground Proximity Warning System - Operational Test__________________________________________________
 A.  References
 (1)  
24-22-00/201, Electrical Power - Control

 (2)  
34-28-01/201, Inertial Reference System

 B.  Access
 (1)  Location Zones
 101/102 Flight Compartment
 205 Electronic Compartment

 C.  Prepare for the Test
 S 865-002
 (1)  
Supply electrical power (Ref 24-22-00/201).

 S 865-003

 (2)  
Make sure this circuit breaker is closed:

 (a)  P18 Circuit Breaker Panel
 1) C629, GROUND PROX WARN

 (3)
Make sure IRS No. 1 is in the NAV mode (AMM 34-28-01/201).

 S 755-004