(d)  
Set signal generator for fly-left indication. Check that HSI course deviation bar and ADI localizer pointer or runway symbol deflect left.

(e)  
Repeat above step for fly-right indication.

(f)  
Repeat steps (b) thru (e) using No. 2 VOR/GS system. Observe VOR RMI wide pointers and first officer's ADI and HSI.

(7)  
Test GS Function

(a)  
Place signal generator approximately 50 feet from glide slope antenna.

(b)  
Tune No. 1 VOR/GS system to 108.1 MHz and signal generator to 108.1-334.7 MHz. Check that captain's ADI and HSI GS flags and pointers appear.

(c)  
Set GLIDE SLOPE control on generator to ON. Check that captain's ADI and HSI GS flags disappear.

(d)  
Place output selector control on signal generator to GS DOWN position. Check that glide slope pointers in captain's ADI and HSI deflect downward.

(e)  
Repeat above step for GS UP position. Check that glide slope pointers deflect upward.

(f)  
Turn off glide slope carrier. Check that GS flags in captain's ADI and HSI come into view.

(g)  
Repeat steps (b) thru (f) using No. 2 VOR/GS system and first officer's ADI and HSI.

(h)  
Remove airplane electrical power if no longer required.

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34-31-0 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/81 

VOR/ILS NAVIGATION SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ B-2509 and B-2510

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 approach beams. Information is also provided of airplane magnetic bearing to the VOR ground 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 antenna, localizer antenna, GS antenna and control panel. Location of the components is shown in Fig. 1. 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, GS and instrument circuit breakers.
C.  VOR/LOC course deviation information is displayed by the course deviation bar in the horizontal situation indicator (HSI) and by the localizer pointer (runway symbol) in the attitude director indicator (ADI). Glide slope (GS) information is displayed by the GS pointer in the ADI and HSI. VOR station bearing information is displayed by pointers in the radio digital distance magnetic indicators (RDDMI). VOR/LOC and GS information is supplied to the flight director computers and to the autopilot. GS deviation information is also supplied to the ground proximity warning system (GPWS) computer. The ADI and HSI are described under 22-11-01, Autopilot/Flight Director System, and the RMI/RDDMI under 34-21-0, Compass System.
D.  Switching is provided to enable either system to feed both captain's and first officer's indicators, flight director computers, the autopilot, and the GPWS computer. Switching is accomplished through the NAV transfer relays, and controlled through the VHF NAV transfer switch.
E.  The NAV and GS warning flags are provided to give an indication of their associated system malfunction. They come into view whenever power is lost to their systems, or whenever the input signals fail, or fall below a certain predetermined value. Warning indicators, to indicate VOR/LOC or GS system malfunctioning, are located on annunciator panels and are described in 34-29-0, Navigation Warning System.
F.  Frequency selection, in a navigation unit, is controlled from the control panel. The GS portion of the unit becomes operative only when a localizer frequency is selected. Localizer frequencies extend from 108.10 to 111.95 MHz, with 40 channels spaced at 50 kHz on the odd tenths megahertz and the odd tenths megahertz plus 50 kHz. Glide slope frequencies range from
329.3 to 335.0 MHz and are paired with the localizer frequencies as shown in Fig. 2. VOR frequencies also spaced at 50 kHz, extend from 108.00 to 118.00 MHz except for the localizer frequencies.
5C8
Jun 20/85 34-31-01 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

L36304K77007
VOR/ILS Navigation System Component Location  5C8 
34-31-01  Figure 1 (Sheet 1)  Oct 20/87 
Page 2 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C8  VOR/ILS Navigation System Component Location 
　
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