ALL  03 Page 13  Oct 10/7334-21-00
 (b)  The heading error signal from the output of the heading error amplifier is detected by the error detector and fed to the fast sync control. Output signals from the fast sync control are fed to the heading error amplifier (through the gain control), and to the superflag control, the frequency control and limiter, and the stepper motor control. This causes the following results when the system enters fast synchronization: 1) Less filtering is provided in the demodulator-filter-
modulator. 2) The gain of the heading error amplifier is decreased. 3) The superflag output becomes invalid. 4) The output of the frequency control and limiter is
 increased.
 5)  The rate of the voltage-to-frequency converter is increased, causing the stepper motor to step at a faster rate.
 6)  The excitation voltage to the stepper motor is increased.

 (6)  
Superflag Control

 (a)  The superflag control normally provides an output for controlling operation of compass flags. The output also controls the clutched control transmitter (CX) steering output and the maintenance flag control. An invalid superflag output disengages the clutch of the clutched CX. The clutch is spring-loaded so that the steering output of the CX will go to a null during the time the superflag output is invalid. This prevents transmission of large error signals to the autopilot. When the superflag output is valid and 28 volts dc is applied to the clutch control, the clutched CX provides steering information to the autopilot. When the superflag output is invalid, the maintenance flag control is disabled. The superflag output will be invalid during any of the following conditions: 1) The servo CT null is off by more than 4 degrees 2) An open rotor winding in the servo CT 3) Loss of INS platform heading signal 4) Loss of INS platform heading valid signal 5) Loss of power to the system 6) System is in fast synchronization mode 7) Loss of magnetic field sensor excitation current

 (7)  
Magnetic Field Sensor Excitation Monitoring

 (a)  The magnetic field sensor excitation monitor (sheet 1, Fig. 5) is enabled in the SLAVED mode only. It monitors the current through the excitation winding of the magnetic field sensor. The output of the magnetic field sensor excitation monitor is applied to the superflag control (sheet 2, Fig. 5) so that when the system is operating in the SLAVED mode and excitation to the magnetic field sensor is lost, the superflag output will become invalid and flags will appear on the HSI and RMI of the affected system.

 EFFECTIVITY

 

 ALL  02 Page 14  Apr 25/8634-21-00
SYNC ANNUN
DB103C
DB302 DB103C
7
POLARITY
DC MAG HDG
STEPPER
+

6 9 ANNUNCIATOR DETECTOR
55
DISPLAY SYS 1

ANNUN
-
MOTOR
7 8 DEMOD
DB103B SHEET 3

AMPL
1 33 -12V DC
800 HZ
HSTEPPER 32

AC SET SLAVE
1 DIODE CW 2 14
CCW5 15
REFERENCE
CVOLTAGE TO MOTOR 33 ASERVO CT X
SQUARE
HEADING DG FREQUENCY RAD NAV

CONTROL CONTROL CONTROL
29NULL ANDRESOFF 4 17 Y

WAVE
CONVERTER DISPLAY SYS 21 30CONTINUITYMATRIX RATE 3 16 672Z

GENERATOR
34-31-0031MONITORLOW 8SET

3 4
1 H
29HDG 9 C 5ISOLATION10 12 AC MAG HDG

HDG
XSERVO11 DC AMPL 1 DISPLAY SYS 2DB103B FV
DEMOD ERROR
YDG MAGNETIC Z AMPL12 22 SHEET 555 ZFILTER AMPL FREQUENCY CDX CTHDG Y 3CT56

MOD CONTROL AND
HX33-11-00 42 B57 LIMITER C
AC X
434
13 39 MAG HDGDB103BSLAVED XZ9 H YINS HDG

3 40 DISPLAY SYS 1 B302 COMPASS CONTROLLER 1
5 C ZSERVODATA RATE

41 SHEET 3 (P5)
3 MAGNETIC HMONITORFIELD 13FAST

GAIN
4426 ACTEST POINTS N-S C 1POWER SENSOR SYNC 14AC CONTROL 11DB107 XEXCITA-CONTROL 10 RADIO NAVY14 2 TION 4 11DC DISPLAY SYS 2

ERROR
ZE-W TEST SUPERFLAGMONITOR 12PWR OFF

34-31-00 POINTS
DETECTOR
HCONTROLAND HDG 51 C22 C13 SWITCHING 52 AC MAG HDG30 X 5SENSOR 4812 DC DISPLAYINS Y|6.8V DC MAINTENANCE 5 49 SYS 1,2VALID MAINT

Z SENSOR FLAG
57PWR SUP FLAG CONTROL 50 SHEET 3 AND 5DB103BDB105

C
H

DB107 X 24H 25 H47 10 Y 2326

X
58

C C Z 2011
27 Y
79

6 21

Z
Z

Z B103 MHR 1 CMPS CPLR (E1-1) 22

C31 4 38Y Y DB104C H

PLATFORM HDG DB303 DB303 DB104C MAG HDG
23 6 3728V DC 55 XX X DISPLAY SYS 2
116 9
12 345 HDG FLAG 7 Y78DC DC 8 35DB104B Z1 33B107 MHR 1 COMPENSATOR (E1-1) 36
B105 MHR 1 FLD H
34-41-07 32 AC5 15 1SNSR (LEFT WING TIP) C

A/P-F/D SAME 2 14
33 CX
　
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航1(122)