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A 737-300/400/500MAINTENANCE MANUAL
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A
737-300/400/500MAINTENANCE MANUAL
STANDBY HORIZON SYSTEM - ADJUSTMENT/TEST
________________________________________
1. General________
A. This procedure contains one task. The task is to do an operational test of the standby horizon system.
TASK 34-25-01-715-001
2. Operational Test - Standby Horizon System_________________________________________
A. Standard Tools and Equipment
(1) Stopwatch - Commercially Available
B. References
(1) 24-22-00/201, Manual Control
C. Access
(1) Location Zones
101 Flight Compartment
D. Prepare for the test
S 865-002
(1)
Supply the electrical power (Ref 24-22-00/201).
S 865-003
(2)
Make sure this circuit breaker is closed:
(a) P18-2 Load Control Center
1) STANDBY HORIZON
S 865-004
(3) Permit sufficient time for the gyro to get to the usual speed of operation.
E. Standby Horizon System Test
S 865-006
(1)
When the power failure flag retracts from view, pull the cage knob and hold it.
S 865-007
(2)
After the indicator becomes stable near the zero pitch and the zero roll position, release the knob quickly.
NOTE: Do not let the knob hit against the indicator front.
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A 737-300/400/500MAINTENANCE MANUAL
(3) S 715-009Wait approximately 3 minutes and make sure the pitch and the roll show | 2.0 degrees of airplane attitude.
(4) S 715-010Open the STANDBY HORIZON circuit breaker and make sure the power failure flag comes into view.
(5) S 715-011After the removal of the power, make sure the indicator continues to show the pitch and the roll | 2.0 degrees for at least 5 minutes.
(6) S 715-012Close the STANDBY HORIZON circuit breaker and make sure the power failure flag retracts from view.
(7) S 865-013Remove the electrical power if it is not necessary (Ref 24-22-00/201).
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1.
2.
3.
A
737-300/400/500MAINTENANCE MANUAL
STANDBY HORIZON SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________
General (Fig. 1)
_______
A. The standby horizon indicator is a backup system for the Inertial Reference System. It functions as a completely independent system which provides its own visual indication of airplane attitude in pitch and roll at all times during flight. The indicator also displays ILS localizer (LOC) and glide slope (G/S) deviation as a backup for those on the EADI.
B. The system consists of the standby horizon indicator located on the center instrument panel (P2).
C. Power for the system is provided from the STBY HRZN circuit breaker, situated on the load control center (P18).
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本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 2(9)
