737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(128)

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A 737-300/400/500MAINTENANCE MANUAL
 (5)  Radio Digital Distance Magnetic Indicator Schematics (Fig. 8)
 (a)  
VOR bearing is displayed by pointers in the RDDMI with the compass card taken as reference. The pointers are connected to the synchro rotors and receiver 26v ac and VOR bearing through the VOR/ADF switches. The pointer flags are biased out-of-view by the VOR valid signal. The ADF/VOR switches are push-on, push-off type and mechanically actuate arrow symbols that annunciate either ADF or VOR legends, depending on mode of operation. The legends ADF/VOR and the associated arrow are lighted by the instrument panel lighting.

 (b)  
The rotor of synchro transmitter B4 is connected to the RDDMI heading gear train. The stator of B4 provides an alternate magnetic heading source for the navigation units.

J1

18

 

VOR/ADF-1 (34-28-00) 26V AC

BEARING
IN (FIG.12)

26V AC SYNCHR0 (FIG.9)

XMTR B4 BEARING-1
MAG HDG TO VALID (FIG.13)
VHF NAV UNITS (FIG.12)
23 COMMON (FIG.9)
26V AC 10
C

(FIG.9)
VOR/ADF-2 BEARING IN (FIG.12)
24
26V AC (FIG.9)
BEARING-2

+5V VALID (FIG.13)
20

LIGHTING
(34-28-00)

21  26 COMMON (FIG.9)
RDDMI SPEERY P/N 4034559-901

Radio Digital Distance Magnetic Indicator Schematic Figure 8
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A
737-300/400/500MAINTENANCE MANUAL
 (6)  VOR/ILS Power Distribution Schematic (Fig. 9)
 (a)  
The VOR/ILS navigation systems receive 28 volts dc and 115 volts ac through circuit breakers as shown in Fig. 9. System No. 1 receives power from the battery bus and the standby bus in panel P18 while system No. 2 is fed from electronic bus No. 2 in panel P6.

 (b)  
The 115 volts ac is stepped down to 26 volts by instrument transformers No. 1 and No. 2. This 26 volts ac is fed to the navigation units for VOR operation and to the RDDMIs for bearing pointer and heading synchro excitation.

 (c)  
The 28 volts dc from the G/S and VOR/LOC circuit breakers are fed to the navigation units. G/S dc powers the glide slope receiver while VOR/LOC dc powers the internal power supply, arms the ILS mode relay, and provides the ILS 28V DC mode voltage output.

 (d)  
The VOR/LOC dc is also fed to the VHF NAV control panel, to relays in the flight instrument accessory unit, and through the HSI VOR/ILS - NAV transfer relays to arm the auto tuning circuits in the VHF NAV control panels. 1) The VOR/LOC dc to the control panel powers the frequency

 displays, the AUTO/MAN annunciators, the test and agility relays, and the manual frequency display shutter bar.
 2)  The VOR/LOC dc to the flight instrument accessory unit is used to energize the test inhibit, and agility relays. VOR/LOC-1 dc is also fed through the accessory unit to the instrument warning approach trigger circuit in the comparator.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

NO. 1 VOR/ILS SYSTEM
VOR/ILS Power Distribution SchematicFigure 9 (Sheet 1)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

NO. 2 VOR/ILS SYSTEM
VOR/ILS Power Distribution SchematicFigure 9 (Sheet 2)

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