1) Make sure the GS flag on the first officer's ADI goes out of view.
2) Make sure the glide slope pointer on the first officer's ADI is in the center.
3) Make sure the VERT flag on the first officer's HSI goes out of view.
4) Make sure the glide slope pointer on the first officer's HSI is in the center.
Open this circuit breaker:
1) P6 Load Control Center - Right a) VOR/LOC-2
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737-300/400/500MAINTENANCE MANUAL
(o)
Set a frequency of 108.10 MHz on the No. 1 VHF NAV control panel.
(p)
Set the VHF NAV transfer switch to the BOTH ON 1 position.
(q)
Adjust the output of the ramp test set to supply glide slope up and glide slope down signals in turn. 1) Make sure the glide slope pointers on the two ADIs follow
the signal change. 2) Make sure the glide slope pointers on the two HSIs follow the signal change.
(r)
Set the VHF NAV transfer switch to the BOTH ON 2 position.
(s)
Close this circuit breaker:
1) P6 Load Control Center - Right
a) VOR/LOC-2
(t)
Open this circuit breaker:
1) P18 Load Control Center - Left
a) VOR/LOC-1
(u)
Set a frequency of 108.10 MHz on the No. 2 VHF NAV control panel.
(v)
Adjust the output of the ramp test set to supply glide slope up and glide slope down signals in turn. 1) Make sure the glide slope pointers on the two ADIs follow
the signal change. 2) Make sure the glide slope pointers on the two HSIs follow the signal change.
(w)
Set the VHF NAV transfer switch to the NORMAL position. 1) Make sure the glide slope pointer on the captain's HSI is in the center.
2) Make sure the glide slope pointer on the first officer's HSI is in the center.
(x)
Close this circuit breaker:
1) P18 Load Control Center - Left
a) VOR/LOC-1
S 865-046
(2)
Turn off the test set and remove it.
(3)
Remove electrical power if it is not necessary (AMM 24-22-00/201).
S 865-047
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737-300/400/500MAINTENANCE MANUAL
VOR/ILS NAVIGATION SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
1. General_______
A. The VHF omnidirectional range (VOR) and instrument landing system (ILS) provides information of airplane position with respect to, and deviation from a selected VOR course, or localizer (LOC) and glide slope (G/S) approach beams. Information is also provided of airplane magnetic bearing to the VOR gound station under reception.
B. Two systems, captain's and first officer's, are installed. Each is comprised of the following components: navigation unit (combined VOR/ILS receiver and instrumentation unit), VOR/LOC antenna, G/S antenna, control panel and a localizer antenna. An accessory unit is shared by both systems. The electronic attitude director indicator (EADI), electronic horizontal situation indicator (EHSI) and radio digital distance magnetic indicator (RDDMI) on each flight instrument panel provide the VOR/ILS navigation displays. Location of the components is shown in Fig. 1. The battery bus and the standby bus in load control center P18 and electronic bus 2 in load control center P6 supply 115 volts ac and 28 volts dc to the VOR/ILS navigation systems through the VOR/LOC and instrument transformer circuit breakers.
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