(c)
When a VOR, DN/RT or UP/LT test is initiated on the control panel, the VOR/LOC super flag to the DAA is interrupted through the test interlock preventing present position update by the FMCS.
(d)
The VOR/LOC super flag signals from both navigation units 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.
(e)
Loading resistors for the navigation unit low flag signals are located in the flight instrument accessory box.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-31-00
ú ú 08B Page 41 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-31-00
ú ú 08B Page 42 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
D41
39+
D43
NAV FLAG
36-
N8 CAPT'S HSI (P1)
D2417+RUNWAY(LOC) FLAG
9-
N25 CAPT'S ADI (P1)
D2457+RUNWAY(LOC) FLAG
9-
N26 F/O'S ADI (P3)
D4539+D47
NAV FLAG36-R305 VOR/ILS-NAVS777 F/O'S HSI
VOR/LOC SUPER FLAG INTERFACE
N9 F/O'S HSI (P3)
XFR RLY-2 (E3-4) XFR SW (P7)
VOR/ILS Flag and ILS 28V DC SchematicFigure 13 (Sheet 1)
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-31-00
ú ú 07B Page 43 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
VOR/LOC AND GLIDE SLOPE FLAG LOADING INTERFACE
VOR/ILS Flag and ILS 28V DC Schematic
Figure 13 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-31-00
ú ú 07B Page 44 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(11) VOR/ILS Deviation Schematic (Fig. 14)
(a)
Fig. 14 shows the VOR/LOC and glide slope deviation interface with the flight instruments and associated systems. The deviation output load switching through the VHF NAV transfer relays is also shown.
(b)
Navigation unit No. 1 normally supplies VOR/LOC and glide slope deviation to the captain's ADI and HSI and glide slope deviation to the ground proximity warning computer. Navigation unit No. 1 signals are also wired directly to flight computer A, flight computer B, and DAA-1. The first officer's instruments are normally supplied from navigation unit No. 2. FCC A, FCC B, and DAA 2 are connected directly to navigation unit No. 2.
(c)
One side of each navigation unit deviation signals are connected directly to the instrument comparator and the other side of the signals through contacts of the VHF NAV transfer relays. This accomodates changes in loading when the transfer circuits are in either BOTH ON 1 or BOTH ON 2 position.
(d)
For an abnormal condition, either pilot's instruments may be switched to the alternate using the VHF NAV transfer switch and relays.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-31-00
ú ú 07B Page 45 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
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(132)
