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 2)
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(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.
(b)
Navigation unit No. 1 normally supplies glide slope deviation to the ground proximity warning computer and to the left EFIS symbol generator. Navigation unit No. 1 signals are also wired directly to flight computer A, flight computer B, DAA-1, and the standby attitude/ILS indicator. The right EFIS symbol generator is normally supplied from navigation unit No. 2. FCC A, FCC B, and DAA-2 are connected directly to navigation unit No. 2.
(c)
For an abnormal condition, the glide slope deviation signals to the ground proximity warning computer and the EFIS symbol generators may be switched to the alternate navigation unit using the VHF NAV transfer switch and relays.
(d)
Navigation unit No. 1 supplies VOR/LOC deviation directly to flight computer A, flight computer B, DAA-1, and the standby attitude/ILS indicator. FCC A, FCC B, and DAA-2 are connected directly to navigation unit No. 2.
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A 737-300/400/500MAINTENANCE MANUAL
M155 VHF NAV UNIT-2 R45 VHF NAV XFRGEN (E2-3)(E3-4) RLY-2(E3-4)
VOR/ILS Deviation Schematic
Figure 14
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(12) VOR/ILS Self-Test Schematic (Fig. 15)
(a)
Fig. 15 shows an interface schematic for the VOR/DME and ILS self-test circuits.
(b)
The VOR and ILS self-tests are inhibited by relays in the accessory unit when the DFCS is operating in an approach mode. Actuation of a VOR, UP/LT or DN/RT self-test completes the flight management system VHF NAV test interlock circuit. The FMC also receives a VOR test discrete when the VOR self-test is actuated on the VHF NAV control panel. The ILS UP/LT self-test is also initiated during the VHF NAV interface test of the DFCS BITE operation.
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A 737-300/400/500MAINTENANCE MANUAL
P8-26 VHF NAV-2 CONT PNL (P8)
VOR/ILS Self-Test SchematicFigure 15 (Sheet 1)
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