(12)
Observe that the FLT CONTROL A LOW PRESSURE light is illuminated.
(13)
Press YES on the YDC BITE panel. Observe that the panel displays TEST PASS.
(14)
Press ON/OFF. Observe that TURN DISPLAY OFF? is displayed on the panel.
(15)
Press YES. Observe that the DISPLAY OFF is temporarily displayed followed by the panel blanking. Observe the AUTOPILOT DISENGAGE WARNING lights are not illuminated.
(16)
Position the FLT CONTROL A switch to OFF.
5. Restore Aircraft to Normal Configuration
A. Disengage yaw damper.
B. Disconnect electrical power. (Ref 24-22-00)
C. Disconnect hydraulic power. (Ref 29-15-00)
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Sep 01/02
YAW DAMPER SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
Aircraft with Yaw Damper Coupler P/N 4084042 (after SB 27A1206)
1. General
A. The successful completion of these tests ensures that the yaw damper system is fully operable. It is assumed that all systems furnishing signal data to the yaw damper are in proper working order and that the rudder control systems are properly rigged.
2. Prepare to Test Yaw Damper System
A. Provide electrical power to aircraft and energize load control center P6 and P18
(Ref 24-22-00).
B. Energize hydraulic systems A and B and ensure FLT CONTROL A and FLT CONTROL B switches are positioned to ON (Ref 29-15-00).
C. Ensure following circuit breakers on load control center are closed.
NOTE: Circuit breakers may vary slightly (or even not be used) from airplane to airplane.
(1)
Panel P6-3
(a)
Indicator Master Dim Bus Bat (C310)
(b)
Indicator Master Dim Bus No. 1 DC (C311)
(c)
Indicator Master Dim Bus No. 2 DC (C312)
(d)
Dim and Test (C133)
(e)
Indicator Master Dim Bus Sect 1 (C313)
(f)
Indicator Master Dim Bus Sect 2 (C314)
(g)
Indicator Master Dim Bus Sect 3 (C315)
(h)
Master Caution Air Cond (C571)
(i)
Master Caution Anti-Ice (C573)
(j)
Master Caution Fuel (C572)
(k)
Master Caution Bus No. 1 (C132)
(l)
Master Caution Bus Bat (C131)
(m)
Master Caution Bus Sect 4 (C316)
(n)
Master Caution Bus Sect 5 (C317)
(o)
Master Caution Bus Sect 6 (C318)
(p)
Yaw Damper AC (C285)
(q)
Yaw Damper DC (C286)
(2)
Panel P6-1
(a) Radio Altimeter-2 AC (if airplane has second altimeter installed) (C321)
(3)
Panel P18-1
(a) Radio Altimeter-1 AC (C302)
(4)
Panel P18-2
(a)
Air Data Computer No. 1 (115 V AC) (C300)
(b)
Air Data Computer No. 1 (26 V AC) (C425)
May 01/00 22-12-01 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
3. Test Yaw Damper System
A. Yaw Damper Configuration and System Tests
NOTE: If no keypad entries are made for 5 minutes, the YDC BITE display will turn off. It will be necessary to start over if this occurs.
(1)
Press ON/OFF. Observe that ENTER BITE? is displayed on the panel.
(2)
Within 10 seconds, press YES. Observe that PLEASE WAIT is temporarily displayed followed by EXISTING FAULTS? on the YDC panel. Observe that the AUTOPILOT DISENGAGE WARNING lights illuminate steadily.
(3)
Press YES on the YDC BITE panel. Ensure that the panel displays NO FAULTS.
NOTE: For aircraft equipped with only one Radio Altimeter System, a “LRRA #2” fault code, message number 22-21037, is a normal condition if Radio Altimeter-2 is not powered or not installed.
(a) If the YDC BITE panel does not display NO FAULTS, then press the down arrow until RESET LATCHES? is displayed. 1) Press YES. 2) When ARE YOU SURE? is displayed on the panel, press YES again. Observe
that RESET IN PROGRESS is displayed on the panel.
3) Wait 10 seconds. The YDC BITE panel will display NO FAULTS or it will display an existing fault. For the purpose of this test, it is irrelevant if a fault is displayed or not.
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