737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(166)

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 2)  AIRPLANES WITH AN INTEGRATED FLIGHT SYSTEM ACCESSORY UNIT; During VOR operation the fin tip VOR/LOC antenna supplies rf through the ILS relays to the navigation units. The nose radome localizer antenna is selected through the ILS relays by mode logic in the DFCS flight computers when making an ILS approach. The logic requires that an ILS frequency be tuned and the DFCS operating in the approach mode; and the VOR to LOC antenna transfer relays in the integrated flight system accessory unit energized. The glide slope antenna elements are connected directly to the navigation units.
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A 737-300/400/500MAINTENANCE MANUAL

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A 737-300/400/500MAINTENANCE MANUAL

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A
737-300/400/500MAINTENANCE MANUAL
 (8)  VOR/ILS Tuning and Mode Select Schematic (Fig. 11)
 (a)  
Tuning of the VOR/ILS and DME systems is controlled either manually or automatically.

 (b)  
MANUAL Mode

 1)  Manual tuning is accomplished on the VHF NAV control panel by actuating the MANUAL mode of operation and then selecting the desired frequency using the frequency selector knobs and manual frequency display. The AUTO frequency display is blanked in manual mode.

 (c)  
AUTO Mode

 1)  The auto tuning mode is armed by 28 volts dc from the associated VHF NAV-1 or -2 VOR/ILS DC circuit breaker. When the AUTO mode on the VHF NAV control panel is actuated, the frequency is automatically selected by the flight management computer (FMC). The DAA unit converts the FMC serial tuning data to a parallel 2-out-of-5 code for tuning the navigation units and the DME interrogators. The MANUAL frequency display is partially blanked by a flag in AUTO mode.
 2)  When the FMC selects agility mode for the DME system, discrete logic is provided to the VHF NAV control panel and to the accessory unit energizing the agility relays. In the control panel, relay K2 causes the AUTO frequency display to display dashes. The agility relay in the accessory unit opens the VOR bearing and VOR valid inputs to the RDDMIs. This causes the associated RDDMI bearing pointers to remain stationary and the pointer flags to come into view.
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FIG.9
FIG.9

P8-25 VHF NAV-1 CONTROL PANEL (P8)

DISPLAY TEST VALUES SHOWN (TWO SECONDS ON, ONE SECOND OFF)
VOR/ILS Tuning and Mode Select SchematicFigure 11 (Sheet 1)
AGILITY MODE
A

FREQ SEL COMMON
VHF
B
NAV
DME (34-55-00)

AUTO TUNE
CNC
NC AUTO TUNE
D
AUTO TUNE FREQ COMM
E
10 MHz
1 MHz

 

NC
MHz0.1
 MHz 0.05
10 MHz
DME AND VHF1 MHzNAV TUNING F
 MHz0.1
 MHz 0.05G/S LOC ENGAGE

G
VOR TESTUP/LT TEST

FMSINTERLOCKFIG. 15 DN/RT TEST
DME TESTCHASSIS GND

A 737-300/400/500MAINTENANCE MANUAL
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