(2)  
Synchronization Mode (Fig. 3)

 (a)  
Prior to yaw axis engagement, the Yaw Damper coupler is in the synchronization mode. The purpose of synchronization is to provide a null output to the electrohydraulic transfer valve to prevent Yaw Damper coupler engage transients.

 (b)  
Synchronization is accomplished by routing the demodulated, parameter-controlled signal from summing point 1 through switch S6, summing point 2 and integrator, and back to summing point 1. Output from summing point 1 results in temporary output from the valve amplifier. The valve amplifier output is reduced to a null as the integrator output increases and cancels the signal at summing point 1. Prior to Yaw Damper engagement, the Yaw Damper actuator remains centered which nulls the position feedback to the Yaw Damper coupler.

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 ú 06 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 6Nov 12/00 

A 737-300/400/500MAINTENANCE MANUAL

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
1
3 33-19-10A 4
D2209AA
D630 D2209A 10
219 8Y/D WARN ANNUNCIATOR 12D319D630 OFF 12S1
17 7 27 9 8
28V DC 26 2 SEC
BUS 1 C286
12
YAW DAMPER

24-30-00 D2209B
S2 50
3
(DC) 2 SEC
DEMODENGAGE
YAW DAMPER
ON NC 2
YAW DAMPER 62
OFF
ENGAGE SW D2209A
114
11
ON
27-20-00

15
5 115V AC
A/P WARN
DEMOD
13
FLT CONT SYS B
LIGHT CKT
C285

ELEX 6 POWER 1 P5-3 FLIGHT CONTROL MODULEYAW DAMPER
(AC)
M1474 INTEG FLIGHT SYSTEM ACCESSORY UNIT (E1-3)7P18 LOAD CONTROLCENTER LEFT (P18-1) N41 YAW DAMPER POSITION INDICATOR (P2)
D295 14 1211 D295
1
HYDRAULIC FLUID
FWD LOC

20
D295 +10V DC
ANT SELECT

61
INTEG
1

| 14.5V DC
POWER | 10V DC

R315 AFCS-ILS ANTENNAD291
5V DC +
2 SUPPLY 1
 18V AC  7
ENGAGE 16 S9
RLY-1 (E3-4) SOLENOID
2
FWD LOC

61 23
4,5
50

ANT SELECT 308
R316 AFCS-ILS ANTENNA  <900 FT = 0
GAIN PROGRAMRLY-2 (E3-4) ROLL56 FUNCTION BANK24 7
+10V DC TRANSFER
2
ATT ANGLE
(AMP NULL
FROM

VALVE
55 S56
NO INPUT)
R/A47
S4
DEMOD

L DAA 10V DC +
32 5 RATE
WASH
FILTER GAIN 1
AMP
M50 LRRA-1 (E2-4) OUT GYRO
VALVEAMP
S68
6
1,6
D309A
3,4,5
63

7 RATE
40
42 2
64
TAKER
65

S8
LAMP TEST TEST READTEST
41 YAW DAMPERDSPLY ACTUATOR
43
PASSM196 DADC-1 (E1-1)
S7
TESTG
S2
8
CIRCUITS
3 DC

RUDDERON
46 11
2 UP

R
PEDAL 47 12
DEMOD
FAIL
5 CHASSIS1 POSITION
OFF  ARM
6 SIGNAL TRANSDUCER ACTUATOR
10
DC +15 DC
S245 TE FLAP

3 1,3 9
4 UP LIMIT SW
9
(STA 715) TEST INPUT

M175 RUDDER POWER17 CONTROL UNIT (PCU)
TEST READOUT(-18 COUPLER)
RUDDER -500 LOGICYaw Damper System SchematicFigure 3 (Sheet 2)
M177 YAW DAMPER COUPLER (E1-3)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (3)  
Engage Interlocks and Logic (Fig. 3)

 (a)  
Prior to engaging the Yaw Damper system, the Yaw Damper disengage warning light is illuminated. Before the Yaw Damper engage switch will remain engaged, the monitor (gate 1) must be good from the 115-volt ac power supply and the flight control B switch must be on.
　
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