(14)
Selecting an up/left or down/right ILS self-test causes the EADI, EHSI and standby attitude/ILS indicator glide slope and localizer pointers to deflect 1 dot up or down and 1 dot left or right when in view. The glide slope and localizer pointers come into view approximately 3 seconds after initiating a test for 23 |5 seconds, then disappear for as long as an ILS self-test is actuated. The standby attitude/ILS indicator G/S and LOC flags disappear when the glide slope and localizer pointers are in view and appear when the pointers are out of view.
NOTE: If the DFCS is in an approach mode, VOR/ILS self-tests are
____
inhibited.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
34-31-02
ú ú 03 Page 17 ú Jul 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
VOR/ILS Navigation System Block Diagram
Figure 3 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH A FLIGHT INSTRUMENT ú
34-31-02
ACCESSORY UNIT ú ú 02 Page 18 ú Jul 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH A FLIGHT INSTRUMENT ú
34-31-02
ACCESSORY UNIT ú ú 06 Page 19 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
VOR/ILS Navigation System Block Diagram
Figure 3 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AN INTEGRATED FLIGHT ú
34-31-02
SYSTEM ACCESSORY UNIT ú ú 02 Page 20 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AN INTEGRATED FLIGHT ú
34-31-02
SYSTEM ACCESSORY UNIT ú ú 01 Page 21 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
(FIG. 14)(FIG. 13)
(FIG. 13)
(FIG. 14)
(FIG. 12)(FIG. 9 AND 13)
(FIG. 12)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
34-31-02
ú ú 01 Page 22 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
C. Functional Description
(1) VOR/ILS Navigation Unit Schematic (Fig. 4)
(a) Collins 51RV Series Navigation Unit
1) The navigation unit power is supplied from two sources, one 28v dc and one 26v ac. VOR/LOC DC powers the power supply, the glide slope receiver, and arms the ILS mode relay. The 26v ac is used for VOR operation.
2) The navigation unit receives VOR/LOC signals in the frequency range of 108.00 to 117.95 MHz. This provides 160 VOR channels and 40 localizer channels with channel spacing of 50 kHz. Glide slope signals are in the frequency range of 329.15 to 335.00 MHz with 40 channels spaced at 150 kHz.
3) VOR/LOC Operation
a) Frequency select information from the control panel is converted to binary-coded-decimal data in the 2x5 monitor. This data controls tuning of the preselectors. The synthesizer provides the required injection frequencies and tuning voltages for the first mixer in the VHF NAV receiver section. Navigation signals are selected by a tuned rf filter controlled by the tuning voltages from the VHF synthesizer. The signals are processed, gain stabilized, and fed to a detector (all within the receive section), which provide receiver signals to the VOR and localizer instrumentaion sections, digital instrumentation section, and drives an audio amplifier in the RMI driver section to provide an audio input to the airplane audio integrating system. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(159)
