737 AMM 飞机维护手册 导航 NAVIGATION 1(80)

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E.  The transfer relay contacts take care of the transfer of signals within the system. In the NORMAL configuration the captain's ADI receives pitch and roll signals from gyro No. 1, but in the CAPT ON AUX position these signals are taken from the auxiliary vertical gyro. The VG Valid signal for the flag logic is also fed to the ADI via the contacts of the transfer relay. In NORMAL it is derived through the contacts of the flag warning relay in vertical gyro No. 1. In the CAPT ON AUX position the VG Valid signals come through the contacts of the flag warning relay in the auxiliary gyro. The auto throttle speed control computer and flight control system channel A also receive pitch and roll signals via the contacts of the transfer relay. The transfer of signals from NORMAL to F/O ON AUX is accomplished in a similar manner. Flight control system channel B and the weather radar input signals may be switched from vertical gyro No. 2 to auxiliary gyro on the first officers side. The ac power source for the auxiliary gyro is the AUX V/G circuit breaker when both systems are in NORMAL, or from the AUX VERT GYRO (ALT) circuit breaker when F/O ON AUX is selected. When the transfer switch is set to CAPT ON AUX, ac power is taken from the AUX V/G (STBY ALT) circuit breaker.
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 Attitude Reference System SchematicOct 20/84 Figure 2 34-22-02Page 5/6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

ATTITUDE REFERENCE SYSTEM - TROUBLE SHOOTING
EFFECTIVITY
GJ B-2509 and B-2510

1.  General
A.  A prerequisite for accurately trouble shooting any system is a good knowledge of normal system operation. Refer to vertical gyro system description and operation for review when required.
B.  To maintain integrity of the vertical gyro system and other associated systems that can be affected when a component is changed, a complete functional test as specified in adjustment/test procedure is required.
C.  When a malfunction occurs in the vertical gyro system and cannot be quickly isolated by substitution of a known serviceable component (s), then a thorough check should be made to determine if correct power is present, at the connector to the component. [Refer to electronic wiring diagrams for pin number(s).]
CAUTION: OBSERVE CORRECT POLARITY TO AVOID DAMAGE TO TEST EQUIPMENT.
D.  If trouble persists after voltage check as in C. above, then check all related connectors for security of connection.
2.  Trouble Shooting Chart
A.  The trouble shooting chart should be used as a guide to help analyze possible source and/or determine the order in which to make tests or substitutions.
5C8
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Attitude display malfunctioning and attitude flag in view Attitude flag in view but attitude display normal Attitude flag does not appear when appropriate circuit breakers are opened Sluggish attitude display movement Attitude display malfunctioning but attitude flag not in view Attitude display out of tolerance with attitude flag removed from view  Vertical gyro inoperative, or attitude director indicator failure Malfunction of VG transfer switch and/or vertical gyro transfer relay Sticking flag Attitude indicator or vertical gyro not functioning properly Attitude indicator Vertical gyro(s) not erecting properly  Check that appropriate circuit breakers are closed. Check valid dc voltage output through vertical gyro interlock (Refer to Wiring Schematic from terminals.) Check Attitude Director Indicator. Check for continuity between vertical gyro relay and vertical gyro transfer switch Check attitude indicator(s) Perform adjustment test Check vertical gyro(s). Check appropriate vertical gyro relay contacts Perform adjustment test  Replace defective attitude director indicator. If trouble still persists, replace defective vertical gyro Replace defective component Replace defective indicator Replace or repair faulty components Replace defective component Replace defective component 

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ATTITUDE REFERENCE SYSTEM -ADJUSTMENT/TEST
EFFECTIVITY
GJ B-2509 and B-2510

1. General
A.  The following procedures describe two methods for testing the attitude reference systems in the airplane. The first procedure is an operational test in which only onboard equipment is used. The second procedure is a system test using the tilt tables to check system tolerances.
B.  The system test should be made prior to or concurrent with the adjustment/test of autopilot, weather radar, flight director, and navigation warning systems. If these systems are to be tested, performing those portions of test which require use of tilt table will save setup time.
　
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