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 B.  One ADI is installed in the center of each pilots' instrument panels, P1 and P3, in the flight control cabin.
 CAUTION: FAILURE TO OBSERVE ELECTROSTATIC DISCHARGE PRECAUTIONARY PROCEDURES
_______ WHEN HANDLING THE ADI MAY RESULT IN DEGRADATION OR FAILURE OF THE ADI.
 C.  Two rear mounted connectors provide an interface of the ADI with airplane wiring.
 D.  Twenty six volt ac is supplied to the ADI power supply to produce dc and ac voltages which power the pitch and roll servocircuits.
 E.  The ATT flag, solenoid controlled, is black letters on a red background and monitors the ADI power source, the pitch and roll servocircuits and the attitude source. In addition, the two ADIs are monitored for pitch and roll comparison by the instrument comparator.
 F.  A test switch on the lower left of the instrument is used to test the attitude indications. Pushing the TEST switch results in the indication of 10 degrees pitch up and 20 degrees right roll with ATT flag in view.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
J1
A
J1PITCH
HH4
DIFF
POWER |DCCC
20
26V ACRESOLVER 5
SUPPLYAC XXPITCH
21 S1 1
Y Y ATT
TY2
ZZCOMPARE
3X
H'H'
PITCH29

6Y
C' C'
ATTITUDE30RS

DEMOD
7
TEST ATTITUDE
INPUT 31

Z
DISPLAYAATTITUDE
J2A +DC TFAILURE
1T
FLAG
-DC J2
ATTITUDEJ128 ATT VALID
VALID 10
J1X
ROLL26
H
YDEMOD H12
ATTITUDE27RS
C
C13X16ROLL
INPUT 28 Z
XJ2
Y
Y 17 ATT
TY
Z
CONT31

TEST Z18COMPARE
H'
H'14
DH
C'
EXC29

S2C' 15
A
ROLL DIFF
A
+DC RESOLVER
TEST 30J2
-DC
4
ROLLLIMITERRATE OF

10 37
COMMAND 20` L/R RATE OFTURN
FLIGHT TURN SHUTTER 38 VALID
DIRECTOR
COMMAND
S3

BAR RATE OF
NULL DET
OFF MODE 53 RATE OF TURN32
TURNF/D FLAG 27 2
<3` = 1 INDICATOR 33
4
COMMAND NULL DET
EXPANDED<3` = 1
F/D FLAG GND 3 S5 CLOCALIZER & RISING
MFLT
RUNWAY INDICATOR
S10 3
PDIR
+
13 RAD ALT
TFLAG R
F/D FLAG 2 -AUX DC
14
IN VIEWS9
DRIVE -DC BIAS (200')
-12V DC 5R/A FLAG
S4
PITCH24

UP5 12200 FOOT
-DC NULL
LIMITER OUT OFS8
DN MONTRIP (GND)
COMMAND 23 20`UP-10`DN +DC -DC
VIEW BIAS
G/S18

DN S6
GLIDE SLOPE
RUNWAY
DEVIATION 19

UP -DC
POINTER
6
7 V/L S FLAG
EXPANDED
+12V DC
20

8 GS
DNLOCALIZER7 GLIDE SLOPEFAILURE
G/S FLAG UP
21FLAG11 ILS DC
FLAG NULLAUTOMON
DN
THROTTLE15
+DC
AIRSPEED

FAST/SLOWS7
UP
16
POINTER
ERROR
S
SPEEDDNP

-DC
COMMANDE

40
+41 UP
34 V/L
FLAG E

-
35 DEV
D
ADI Schematic
Figure 12

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 G.  The pitch and roll servocircuits are similar, consisting of an input resolver, a demodulator, a servoamplifier and a motor. The input resolvers sense a three wire attitude signal input which is resolved into a sine and cosine output. The sine signal is converted to dc, which drives the motor and the horizon to the appropriate position and repositions the resolver to null the sine signal. The cosine signal of the resolver is applied to the flag circuit.
 H.  The flag circuit consists of an AND gate, a solenoid and the ATT flag. When the attitude source is valid, the servodrives are normal and excitation is sensed from the cosine output of the resolvers, the AND gate output is high, the flag solenoid is energized and the ATT flag retracts.
　
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