B. Standby Horizon Indicator The standby horizon indicator is supplied with 28VDC from essential bus 401PP. A static inverter in the instrument converts this 28VDC into three phase alternate current to supply the gyroscopic motor. The gyro rotor rotates at high speed (> 23,000 RPM) around its vertical axis and provides the vertical reference. The gimbal assy comprises two orthogonal axes (pitch and roll). The internal gimbal which includes the stator controls the rotation of the drum in the pitch axis by means of gear. The pitch gimbal is restricted to approximately plus or minus 85 degrees around the pitch axis (mechanical stop). The external gimbal controls the roll rotation. The roll gimbal has unrestricted 360 degrees rotation around the roll axis. The gyro pin axis is maintained in the vertical position by the erection system (unstable pendulum erector) which is removed when the rotor axis deviates more than 9 degrees plus or minus 2 degrees. The accuracy of the vertical position in clean configuration is less than 0.5 degree. The fast resetting of the gyroscopic horizon can be activated by pulling the knob (8) located in the lower R corner of the indicator. The indicator provides the following information :
-roll angle,
-pitch angle,
-instrument failure (RED flag).
(1)
Pitch information The aircraft symbol (black and yellow) (7) is fixed. The pitch drum (9), in the center of the instrument is divided into two zones separated by the reference horizon (white) : the upper part is blue, the lower part is brown. The pitch indications are displayed by means of a drum which is graduated between -80 and +80 degrees.
(2)
Roll information The roll information is given by a pointer (10) which moves in front of a dial (5) graduated in 10 degrees increments between -30 and +30 degrees.
(3)
Failure warning The flag (6) comes into view if a failure is detected in the electrical power supply or if the gyro rotor speed drops below 18,000 RPM.
1EFF : 213-213, 1 34-22-00Page 2 1 1 Config-3 Nov 01/03 1 1 1CES 1
Standby Data - Attitude and Heading - Component Location
Figure 001
1EFF : 213-213, 1 34-22-00Page 3 1 1 Config-3 Nov 01/03 1 1 1CES 1
Standby Data - Attitude and Heading - Electrical Circuit
Figure 002
1EFF : 213-213, 1 34-22-00Page 4 1 1 Config-3 Nov 01/03 1 1 1CES 1
Standby Data - Attitude and Heading - Data Indicating
Figure 003
1EFF : 213-213, 1 34-22-00Page 5 1 1 Config-3 Nov 01/03 1 1 1CES 1 STANDBY DATA : ATTITUDE AND HEADING - ADJUSTMENT/TEST
_____________________________________________________
TASK 34-22-00-710-001
Operational Check of the standby compass including light test and visual check
WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.
1. Reason for the Job
__________________
R Refer to the MPD TASK: 342200-01 R To make sure that:
-
the difference between the magnetic heading values on the standby compass and the ND is not more than + or - 8.
-
the lighting of the standby compass operates correctly
-you can read the compass cards .
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure 34-10-00-860-004 IR Alignment Procedure 34-22-00-730-001 Compensation Adjustment/Test of the Standby Compass
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