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A 737-300/400/500MAINTENANCE MANUAL
(9) VOR Audio, Bearing, Course Select and To/From Schematic (Fig. 12)
(a) Fig. 12 shows the VOR audio, bearing, course select and to/from signal interface with the flight instruments, the DAA units, and the DFCS mode select panel. 1) The navigation units normally receive magnetic heading from
heading repeater synchro transmitters in the RDDMI's. Navigation unit No. 1 receives magnetic heading from the captain's RDDMI while the first officer's RDDMI supplies magnetic heading to navigation unit No. 2.
2) The VOR bearing sine and cosine outputs from navigation units No. 1 and 2 are connected directly to DAA 1 and 2 respectively. The aux navigation unit VOR bearing sine and cosine outputs are not used.
3) Course selection is controlled by the left and right COURSE select knobs and counters in the DFCS mode select panel. The DFCS course select circuits are connected directly to the navigation units and through the VOR/ILS - NAV transfer relays to the HSI's. Each knob drives a course counter and positions the rotors of a control differential transmitter (CDX) and a synchro resolver in the mode select panel. The CDX receives magnetic heading from the IRS (AMM 34-28-00) to provide the input signal to a servo-amplifier in the HSI. The servo-amplifier drives the HSI course arrow to the course selected on the DFCS mode control panel. The resolver rotors receiver 26 volts ac inputs from the navigation unit to provide bearing sine and cosine outputs to the navigation unit. The sine and cosine inputs are used by the navigation units to compute the VOR deviation and to/from outputs. The to/from output is applied to the HSI through the VHF NAV transfer relays to indicate if the selected course is to or from the VOR station.
4) The to/from output is applied to the HSI through the VHF NAV and VOR/ILS - NAV transfer relays to indicate if the selected course is to or from the VOR station.
5) Audio from each navigation unit is applied to the audio integrating system.
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6) VOR bearing is applied through the agility relays in the flight instrument 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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A 737-300/400/500MAINTENANCE MANUAL
M155 VHF NAV UNIT-2 (E3-4)
DFCS COURSE SELECT AND MAGNETIC HEADING INTERFACE
VOR/ILS Audio, Bearing, Course Select and To/From SchematicFigure 12 (Sheet 1)
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A 737-300/400/500MAINTENANCE MANUAL
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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 and ILS 28V DC to the captain's ADI and HSI, to the flight computer (FCC) A, the digital to analog adapter (DAA) 1, the ground proximity computer and the instrument comparator. Navigation unit No. 2 normally supplies the identical signals to the first officer's ADI and HSI, FCC B, DAA-2, and the instrument comparator. Either pilot's instruments, the ground proximity computer and the instrument comparator may be switched to the alternate receiver for abnormal conditions.
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本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(131)
