(a)  
Set BITE switch to ARM. Verify that: 1) PASS light illuminates 2) TEST number displays 0 3) A/P WARN lights illuminate steady

 (b)  
Press LAMP test. Verify that:
 1) PASS and FAIL lights illuminate
 2) TEST number displays 8

 (c)  
Release LAMP TEST. Verify that:
 1) PASS light remains illuminated
 2) TEST number displays 0

 (5)  
Each time the GO switch is pressed, the PASS and FAIL lights extinguish. When the GO switch is released, the test is initiated and the TEST number increments up by one.

 D.  Yaw Damper BITE Tests (Fig. 3)
 (1)  
A test signal is injected at the circle for the number of the test and read at the respective square. If the correct output is read, the PASS light illuminates. If the time expires and the output is not present, the FAIL light illuminates.

 (2)  
Unless otherwise noted, the following conditions are assumed for each test:

 (a)  
The Yaw damper is engaged.

 (b)  
Hydraulics are on.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH 10-60447 YAW DAMPER ú

 22-12-00
 COUPLER  ú
 ú 05 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 10Mar 15/99 

A
737-300/400/500MAINTENANCE MANUAL
 (3)  
Test 1 - Rate Gyro Filter 1

 (a)  Press and release GO. A stimulus is applied to the rate gyro filter input at test input 1 which drives the valve amplifier. Rudder position is read at test readout 1. Test time is approximately 1 second.

 (4)  
Test 2 - Engage Null

 (a)  Press and release GO. The stimulus at test input 1 is removed and the valve amplifier output is read at test readout 2. Test time is approximately 5 seconds.

 (5)  
Test 3 - Rate to Rudder (Displacement)

 (a)  Press and release GO. A stimulus is applied to test input 3 at the valve amplifier which drives the rudder. Rudder position feedback is read at test readout 3. Test time is approximately 1 second.

 (6)  
Test 4 - Rate to Rudder (Integral)

 (a)  Press and release GO. A stimulus is applied to test input 4 at the valve amplifier which drives the rudder. Rudder position feedback is integrated and read at test readout 4. Test time is approximately 40 seconds.

 (7)  
Test 5 - Disengage Synchronization

 (a)  The Yaw Damper is disengaged, hydraulics are turned off and GO is pressed and released. A stimulus is applied to test input 5 at the valve amplifier. The valve amplifier output is synchronized and the integrator output read at test readout 5. Test time is approximately 5 seconds.

 (8)  
Test 6 - Derived Accel. First Stage

 (a)  The Yaw Damper is disengaged, hydraulics are turned off and GO is pressed and released. The stimulus at test point 5 is removed and 10v dc signal is applied to the demodulation amplifier. The derived acceleration output is read at test point 6. Test time is approximately 1 second.

 (9)  
Test 7 - Rate Gyro Filter 2

 (a)  The Yaw Damper is disengaged, hydraulics are turned off and GO is pressed and released. The stimulus at test point 6 is removed. A stimulus is applied to the airspeed gain circuit and read at the input to the valve amplifier at test readout 7. Test time is approximately 1 second.

 (10)
 Test 8 - Rate Gyro

 (a)  
The Yaw Damper is disengaged, hydraulics are off and GO is pressed and released. The stimulus at test input 7 is removed and the rate gyro is torqued. The rate gyro demodulator output is read at test readout 8. Test time is approximately 1 second. Torquing stimulus is removed from the rate gyro at the end of the test.

 (b)  
If the GO switch is pressed and released after test 8, the BITE test returns to 0.

 (c)  
The BITE switch is returned to OFF at the end of the tests. The hydraulics are applied and the Yaw Damper coupler is engaged for normal operation.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH 10-60447 YAW DAMPER ú

 22-12-00
 COUPLER  ú
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 2(72)