H24332
Directional Gyro Installation 502
34-21-21 Figure 401 May 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Connect external electrical power or use APU power.
E. Check that all compass system and instrument transformer circuit breakers are closed.
F. Place compass transfer switch to NORMAL (if installed).
G. Allow 10 minutes for the system to stabilize and check that the RMI and CDI (HSI) compass warning flags are out of view.
H. Rotate captain's RMI SYNC knob in direction of dot; compass card should rotate clockwise and annunciator should rotate toward plus sign. Rotate knob through synchronization in direction of plus sign; compass card should rotate counterclockwise and annunciator should rotate toward dot.
I. Repeat step H using first officer's RMI SYNC knob.
J. Disconnect electrical power.
502
Nov 1/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-21-21 Page 403
ATTITUDE REFERENCE SYSTEMS - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The attitude reference system is designed primarily to furnish the captain and first officer with information concerning the airplane's attitude in both pitch and roll axes at all times during flight. It also provides pitch and roll displacement signals to the autopilot, flight director systems, comparator and weather radar antenna stabilization system. Two systems are installed; system No. 1 feeding information to the captain's ADI, flight director steering computer No. 1, flight recorder and autopilot; while system No. 2 feeds information to the F/O ADI, flight director steering computer No. 2, and weather radar.
B. Each system consists of the following components; vertical gyro, roll servo-amplifier, pitch servo-amplifier, warning flag logic circuit, and attitude director indicator. The amplifiers, plus an excitation transformer for the servo circuits are contained in the instrument amplifier unit, and the location of all components is shown in Fig. 1.
C. Power to withdraw the warning flag from view in each ADI is generated in the warning flag logic circuit for that system. The warning flag will appear when power is lost to the instrument amplifier, or if the flag logic circuit loses its reference from the vertical gyro fail logic, or in the event of a malfunction in either pitch or roll servo-amplifier circuits.
D. The VERTICAL GYRO transfer switch operates a transfer relay that connects the captain's ADI to either gyro reference. With the transfer switch in NORMAL position, the captain's ADI is referenced to vertical gyro No. 1 and the F/O's ADI is referenced to vertical gyro No. 2. With the transfer switch in BOTH ON 1 position, both ADI's are referenced to vertical gyro No. 1. With the transfer switch in BOTH ON 2 position, both ADI's are referenced to vertical gyro No. 2.
2. Vertical Gyro
A. The gyro has 360 degrees of freedom about the roll axis, and . 85 degrees of freedom about the pitch axis. Initial erection of the gyro is accomplished by internal circuits, and no manual caging device is used. The erection system maintains verticality within 1/4 degree during unaccelerated flight and within 1 degree during maneuvers; or in turbulent air.
5C8
Jun 20/85 34-22-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
K77827
Attitude Reference System Component Location 5D8
34-22-0 Figure 1 Jun 20/86
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