(5)
Yaw Damper Coupler (P/N 4030952-902) BITE Tests (Fig. 2)
591
22-12-0 Page 10 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/83
NOTE: The following test descriptions are typical and may not represent the latest test procedures due to design improvements.
(a)
Unless otherwise noted, the following conditions are assumed for each test: 1) Yaw damper is engaged. 2) Hydraulics are on.
(b)
Test 1 - Rate Gyro Filter
1) GO is pressed. A stimulus is applied to the rate gyro input at 1 which drives the valve amplifier. Rudder position is read at 6. Test time is approximately 1 second.
(c)
Test 2 - Engage Null
1) GO is pressed. The stimulus at input 1 is removed and the valve amplifier output is read at 3. Test time is approximately 5 seconds.
5C1
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-12-0 Page 11
T51971
591
22-12-0 Page 12 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/80
(d)
Test 3 - Rate to Rudder (Displacement)
1) GO is pressed. A stimulus is applied to input 3 at the valve amplifier which drives the rudder. Rudder position feed back is read at 4. Test time is approximately 1 second.
(e)
Test 4 - Rate to Rudder (Integral)
1) GO is pressed. A stimulus is applied to input 3 at the valve amplifier which drives the rudder. Rudder position feedback is integrated and read at 1. Test time is approximately 45 seconds.
(f)
Test 5 - Trim Meter
1) GO is pressed. The stimulus at input 3 is removed and the rudder position feedback signal to the trim meter amplifier is read at 5. Test time is approximately 8 seconds.
(g)
Test 6 - Disengage Synchronization
1) The yaw damper is disengaged, hydraulics are turned off and GO is pressed. A stimulus is applied to input 3 at the valve amplifier. The valve amplifier output is synchronized and the integrator output read at 1. Test time is approximately 5 seconds.
(h)
Test 7 - Rate Gyro
1) The yaw damper is disengaged, hydraulics are off and GO is pressed. The stimulus at input 3 is removed and the rate gyro is torqued. The rate gyro demodulator output is read at 2. Test time is approximately 1 second. Torquing stimulus is removed from the rate gyro at the end of the test.
2) The BITE switch is returned to OFF at the end of the tests. Hydraulics are applied and the yaw damper coupler is engaged for normal operation.
(6) Yaw Damper Coupler (P/N 4030952-906) BITE Tests (Fig. 2, Sheet 2).
NOTE: The following test descriptions are typical and may not represent the latest test procedures due to design improvements.
(a)
Unless otherwise noted, the following conditions are assumed for each test: 1) Yaw Damper is engaged. 2) Hydraulics are on.
(b)
Test 1 - Rate Gyro Filter 1
1) GO is pressed. A stimulus is applied to the rate gyro input at 1 which drives the valve amplifier. Rudder position is read at 5. Test time is approximately 1 second.
(c)
Test 2 - Engage Null
1) GO is pressed. The stimulus at input 1 is removed and the valve amplifier output is read at 3. Test time is approximately 5 seconds.
(d)
Test 3 - Rate to Rudder (Displacement)
1) GO is pressed. A stimulus is applied to input 3 at the valve amplifier which drives the rudder. Rudder position feed back is read at 4. Test time is approximately 1 second.
(e)
Test 4 - Rate to Rudder (Integral)
1) GO is pressed. A stimulus is applied to input 3 at the valve amplifier which drives the rudder. Rudder position feedback is integrated and read at 1. Test time is approximately 40 seconds.
(f)
Test 5 - Disengage Synchronization
1) The yaw damper is disengaged, hydraulics are turned off and GO is pressed. A stimulus is applied to input 3 at the valve amplifier. The valve amplifier output is synchronized and the integrator output read at 1. Test time is approximately 5 seconds.
(g)
Test 6 - Derived Acceleration First Stage
1) The yaw damper is disengaged, hydraulics are turned off, and GO is pressed. The stimulus at input 3 is removed and a 10v dc stimulus is applied to input 4 at the demodulation amplifier. The derived acceleration output is read at 6. Test time is approximately 1 second.
(h)
Test 7 - Rate Gyro Filter 2
5C1
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-12-0 Page 13
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) AUTO FLIGHT 自動(dòng)飛行 2(44)
