737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(25)

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 12. Flight Instrument Switching (Fig. 15, 16, and 17)
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 A.  The HSI's, ADI's, and RDDMI's are multipurpose instruments used to display flight information from several different sources. Because of this, IRS information is transferred to these instruments through a flight instrument switching network. The various switching relays are located on the E1-2 and E3-4 equipment shelves.
 B.  The transfer switching for the IRS heading output data is shown in Fig. 15. The heading output signals from DAA-1 are normally applied to the Captain's HSI and RDDMI and the heading output signals from DAA-2 to the First Officer's HSI and RDDMI.
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A
737-300/400/500MAINTENANCE MANUAL
26V AC
26V AC
HDG
MAG
HDG
VALID

GND
COMMON
26V AC
+5V LIGHTING
COMMON
26V AC
26V AC
STATUS OUT
VALID IN

CLOCK
WORD
SYNC
DATA
CLOCK
WORD
SYNC
DATA
STATUS OUT
VALID IN

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A 737-300/400/500MAINTENANCE MANUAL

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Attitude Power and Analog Interface SchematicFigure 16
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N6 CAPT RDDMI (P1) Attitude and Compass Flag Interface Schematic Figure 17
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737-300/400/500MAINTENANCE MANUAL
 C.  The transfer switching for the IRS attitude output data is shown in Fig. 16. The attitude output signals from DAA-1 are normally applied to the Captain's ADI and from DAA-2 to the First Officer's ADI. The attitude transfer switch can be used to supply attitude data to both ADI's from DAA-1 or to both ADI's from DAA-2.
 D.  The DAAs supply heading warning and attitude valid signals to the flight instruments (Fig. 17). The valids are applied through contacts of the transfer relay and the associated transfer switches. The valids monitor the operation of the instruments, the operation of the transfer switch and its associated relays, and the source of the information, the associated DAA and IRU.
 13. IRS Power Interface (Fig. 18)
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 A.  Power for the IRS system is derived from the standby bus, electronics power No. 2 bus, 28-volt dc bus No. 1, and switched hot battery bus. Control is through the electronic circuit breaker panels P18 (for system No. 1) and P6 (for system No. 2).
 B.  The system is energized by closing all IRS and DAA circuit breakers on the two circuit breaker panels. System power includes 115-volt ac primary power and 28-volt dc backup power.
 C.  When airplane power fails, the IRU automatically switches to battery power. IRS No. 2 stays on battery power for a maximum of 340 |40 seconds (5 minutes) and turns off if primary power is not restored within this period. IRS No. 1 stays on battery power indefinitely.
　
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