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A
737-300/400/500MAINTENANCE MANUAL
 (3)  Horizontal Situation Indicator Schematic (Fig. 6)
 (a)  
The indicator internal power supply uses the airplane 26 volts ac electrical power to develop all dc voltages required by the indicator with the exception of the panel lights. The panel lights use the airplane 5 volt ac panel light power.

 (b)  
Inputs to the HSI for developing the VOR/ILS navigation system displays are course select from the DFCS data bus, glide slope and VOR/LOC deviation, VOR TO/FROM, mode discretes which annunciate whether the HSI navigation displays are operating in the NAV or VOR/ILS mode, and flag (valid) signals which control flags and shutters.

 (c)  
The HSI VOR/ILS - NAV and 1-2-3 data source annunciators, the glide slope deviation and to/from pointers, the course deviation bar, and the nav and VERT (glide slope) warning flags are meter driven.

 (d)  
The course arrow is driven by a servo-amplifier loop. A change in the course select signal to resolver B1 causes an error signal to be applied to amplifier A6. The amplifier output drives motor B7 to position the course arrow to the selected course and the rotor of resolver B1 to null the course select servo-amplifier loop. The course arrow then displays the selected course read against the HSI compass card.

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 34-31-00

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A 737-300/400/500MAINTENANCE MANUAL

N  V  I 
A  O  L 

V  R  S 

J1
VOR/ILS-NAV
ANN (FIG 10)

2
DATA SOURCE ANN (FIG 10)

3
COURSE SELECT (FIG 12)
J2

UP 5
GS DEV (FIG 14) DOWN 6
TO 1
TO-FROM (FIG 12) FROM 2
COURSE
RIGHT 3 DEV
LEFT 4(FIG 14)
NAV FLAG

-(FIG 13)

J1

+

+ (FIG 13) GS FLAG

J2

-
26V AC

H
SEL HDG PWR

C
(34-28-00)
5V AC PANEL

H
LIGHTING (33-11-00)

C
Horizontal Situation Indicator Schematic
Figure 6

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (4)  Attitude Director Indicator Schematic (Fig. 7)
 (a)  
The localizer and glide slope deviation displays on the ADI are driven by inputs from the navigation unit.

 (b)  
The runway symbol is driven horizontally to show localizer deviation and vertically to indicate radio altitude (R/A) from 200 feet to touchdown. The indicator is initially driven into view by ILS frequency selection and a valid navigation unit (V/L S FLAG) enabling gate B, which opens S1 and S6 and supplies gate A with logic 1. The VOR/LOC deviation drives the indicators through a servomotor. With a valid radio altimeter and 200 feet R/A sensed, gate A opens S2, enabling R/A AUX DC drive to operate the indicator in a vertical direction. Gates C and D monitor servo operation and flags to retract the runway flag for normal operating conditions.

 (c)  
The glide slope pointer is driven by a meter movement. The glide slope super flag signal energizes a solenoid to bias the GS flag out of view which indicates a valid glide slope deviation display.

28V AC
FROM IRS
(34-28-00)

FROM LRRA

GLIDE SYSTEM

FIG.
B18 SLOPE

(34-48-00)
14 ATION DEVI-B19

V/L S FLAG B7
FIG.13
ILS DC B11 + GLIDEB20

FIG.
SLOPE 13B21 FLAG

V/LFIG.14
DEV
Attitude Director Indicator Schematic
Figure 7

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