B. Procedure
S 862-008
(1) Open these circuit breakers and attach the DO-NOT-CLOSE tags:
(a) P18 Load Control Center
1) STANDBY HORIZON
S 022-010
CAUTION: PERMIT 9 MINUTES FOR GYRO TO STOP AFTER THE REMOVAL OF THE
_______ ELECTRICAL POWER. THIS WILL PREVENT DAMAGE TO THE GYRO IN THE INDICATOR DURING REMOVAL FROM THE INSTRUMENT PANEL.
THIS IS A DELICATE INSTRUMENT. HANDLE WITH THE GREATEST CARE.
(2) Do these steps to remove the standby attitude indicator:
(a) Pull the knob out from the face of the indicator and install the lock device to cage the standby attitude display.
NOTE: This step is optional.
____
(b)
Loosen the two larger indicator clamp screws adjacent to the indicator.
(c)
Pull the indicator from the instrument panel to get to the electrical connector.
(d)
Disconnect the electrical connector from the indicator.
S 552-011
(3) Put the indicator on a soft, level surface.
TASK 34-25-11-402-012
4. Install The Standby Horizon Indicator
_____________________________________
A. Reference
(1) AMM 24-22-00/201, Manual Control
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A
737-300/400/500MAINTENANCE MANUAL
B. Access
(1) Location Zone
101 Flight Compartment
C. Procedure
S 862-014
(1) Make sure these circuit breakers are open with the DO-NOT-CLOSE tags attached:
(a) P18 Circuit Breaker Panel
1) STANDBY HORIZON
S 422-015
(2) Do these steps to install the standby attitude indicator:
(a)
Connect the electrical connector to the indicator.
(b)
Move the indicator into the instrument panel.
(c)
Tighten the indicator clamp screws.
(d)
Remove the lock device (if installed) from the knob on the standby attitude indicator.
S 862-016
(3) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P18 Load Control Center
1) STANDBY HORIZON
D. Standby Horizon Indicator Test
S 862-017
(1)
Supply electrical power (AMM 24-22-00/201).
S 712-018
(2)
Make sure the panel lights for the standby attitude indicator are on.
(3)
Make sure the standby attitude indicator flag disappears.
S 862-019
(4)
Remove the electrical power if it is not necessary
(AMM 24-22-00/201).
S 712-026
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737-300/400/500MAINTENANCE MANUAL
INERTIAL REFERENCE SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
1. General (Fig. 1 and 2)_______
A. The inertial reference system (IRS) provides inertial navigation data to user systems. It uses a ring laser gyro instead of the conventional rate gyro to sense angular rate about the roll, pitch and yaw axes. The system is termed strapdown since its sensors are, in effect, directly mounted to the airframe.
B. The inertial reference system (IRS) includes two inertial reference units (IRU), one inertial system display unit (ISDU), one mode select unit (MSU), one master caution unit (MCU) and two digital/analog adapters (DAA). The system provides inertial navigation and flight control data to other systems (Fig. 2).
C. The main function of each IRU is to sense and compute linear accelerations and angular turning rates about the airplane's pitch, roll, and yaw axes. This data is used for pitch and roll displays and navigational computations.
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