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A 737-300/400/500MAINTENANCE MANUAL
RADIO DIGITAL DISTANCE MAGNETIC
INDICATOR (RDDMI)
ATTITUDE DIRECTOR INDICATOR (ADI) HORIZONTAL SITUATION INDICATOR (HSI)
VOR/ILS Navigation System Component Location
Figure 1 (Sheet 3)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
108.10
108.15
108.30
108.35
108.50
108.55
108.70
108.75
108.90
108.95
109.10
109.15
109.30
109.35
109.50
109.55
109.70
109.75
109.90
109.95
110.10
110.15
110.30
110.35
110.50
110.55
110.70
110.75
110.90
110.95
111.10
111.15
111.30
111.35
111.50
111.55
111.70
111.75
111.90
111.95 334.70
334.55
334.10
333.95
329.90
329.75
330.50
330.35
329.30
329.15
331.40
331.25
332.00
331.85
332.60
332.45
333.20
333.05
333.80
333.65
334.40
334.25
335.00
334.85
329.60
329.45
330.20
330.05
330.80
330.65
331.70
331.55
332.30
332.15
332.90
332.75
333.50
333.35
331.10
330.95
NOTE:VOR FREQUENCIES SPACED AT 50-kHz RANGE FROM 108.00 TO 117.95 MHz EXCEPT FOR THE ABOVE LOCALIZER FREQUENCIES.
ILS Frequency Chart
Figure 2
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A
737-300/400/500MAINTENANCE MANUAL
(4)
The left swing-out mounting frame supports the VOR/LOC receiver board and the glide slope receiver board. Each board contains tuner, synthesizer, self-test, and injection oscillator circuitry. The VOR/LOC receiver is on the outer board and the glide slope receiver is on the inner board.
(5)
The right swing-out mounting frame supports board for interconnections and the remaining VOR/ILS circuits. The VOR/LOC instrumentation and 2 out of 5 circuits, and optional expanded VOR monitor, programmable bearing filter, and digital bearing output circuits are on the inner board. The glide slope instrumentation, digital instrumentation, and optional VOR/ILS self-test and expanded ILS monitor circuits are on the outer board.
3. VHF NAV Control Panel_____________________
A. The controls for each navigation unit are on separate NAV control panels. The controls on each panel consist of an AUTO/MAN mode select switch/indicator with associated liquid crystal frequency displays, two concentric frequency selector knobs, and two test switches.
B. The manual and automatic tuning modes are selected by the AUTO/MAN switch/indicator which illuminates to indicate the selected mode.
C. The frequency selector knobs provide manual tuning of the associated VOR/ILS navigation unit and the DME interrogator. The small knob controls the tenths and hundredths digits while the large knob controls the units and ten digits displayed by the MANUAL frequency display.
D. The MANUAL frequency display indicates VOR/ILS frequency channels spaced at 50 kHz between 108.00 and 117.95 MHz. A bar appears across the display while in the auto mode. The MANUAL frequency display can be preset to another frequency while in the auto mode by using the manual frequency selector knobs.
E. The AUTO frequency display is blank during manual mode of operation. In the AUTO mode, the display indicates frequencies between 108.00 and
117.95 MHz as programmed by the Flight Management Computer System (FMCS) (AMM 34-62-00). The AUTO frequency display indicates dashes during FMCS agility mode.
F. The frequency displays and AUTO/MAN mode annunciators are tested through the airplane lighting master dim and test circuits. When the master TEST switch is actuated, both AUTO/MAN mode annunciators illuminate and the frequency displays flash 188.88, alternating 2 seconds on and 1 second off.
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