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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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