737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(168)

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 4)  Audio from each navigation unit is applied to the audio integrating system.
 5)  VOR bearing is applied through the agility relays in the accessory unit to the RDDMI bearing pointers. During DME agility mode, the agility relay is energized, disabling the RDDMI bearing pointer movement.
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 ú ú 06 Page 50 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

M155 VHF NAV UNIT-2 (E3-4)
VOR/ILS VOR Audio, Bearing and Course Select SchematicFigure 12 (Sheet 1)

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 ACCESSORY UNIT  ú ú 07 Page 51 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.

M155 VHF NAV UNIT-2 (E3-4)
SEE FIG. 11 FOR AGILITY MODE
RELAY CONTROL CIRCUITS

1
VOR/ILS VOR Audio, Bearing and Course Select Schematic
Figure 12 (Sheet 2)

A 737-300/400/500MAINTENANCE MANUAL
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 SYSTEM ACCESSORY UNIT  ú ú 07 Page 52 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (10) VOR/ILS Flag and ILS 28V DC Schematic (Fig. 13)
 (a)  
Fig. 13 shows the VOR/LOC and glide slope super flag and ILS 28 volt dc mode voltage interface with the flight instruments and associated systems.

 (b)  
Navigation unit No. 1 normally supplies the flag outputs to the standby attitude/ILS indicator, to the flight computer (FCC) A, the digital to analog adapter (DAA) 1, the ground proximity computer and the left EFIS symbol generator. Navigation unit No. 2 normally supplies the identical signals to the FCC B, DAA-2, and the right EFIS symbol generator. The ground proximity computer and the EFIS symbol generators may be switched to the alternate receiver for abnormal conditions.

 (c)  
ILS 28v dc from navigation unit No. 1 is applied to DAA-1, FCC A, the left EFIS control panel, the standby attitude/ILS indicator, and to ILS relay 1. Navigation unit No. 2 supplies ILS 28v dc to DAA-2, FCC B, the right EFIS control panel, and to ILS relay 2.

 (d)  
The VOR/LOC super flag signals are applied to both RDDMIs to control their respective pointer flags. When the agility mode is initiated, the flag signals are interrupted, allowing the RDDMI pointer flags to show.

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 ú ú 05 Page 53 ú Nov 12/01

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
D357
VOR/LOC S FLAGB50

G/S S FLAGA27
ILS 28V DCB38

 

M154 VHF NAV UNIT 1(E3-4)
D359
ILS 28V DC B38

G/S S FLAGA27
VOR/LOC S FLAG B50M155 VHF NAV UNIT 2(E3-4)

VOR/ILS Flag and ILS 28V DC SchematicFigure 13 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH A FLIGHT INSTRUMENT ú

 34-31-02

 ACCESSORY UNIT  ú ú 05 Page 54 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
D357
VOR/LOC S FLAGB50

G/S S FLAGA27
ILS 28V DCB38

 

M154 VHF NAV UNIT 1(E3-4)
D359
ILS 28V DC B38
　
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