H28668
Rudder Solenoid and Transfer Valve Installation 580
22-12-21Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/79
RUDDER SOLENOID AND TRANSFER VALVES - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on
1. Rudder Solenoid and Transfer Valve Tests
A. General
(1) This test ensures that the solenoid and transfer valves operate properly and assumes the rest of the yaw damper system is operating normally.
B. Prepare to Test Valve
(1)
Pressurize hydraulic systems A and B (Ref 29-11-0, Hydraulic System A, and 29-12-0, Hydraulic System B - MP).
(2)
Provide electrical power and close yaw damper circuit breakers on P6 panel.
C. Test Rudder Solenoid Valve (Aircraft not incorporating SB 27A1206)
(1)
Place yaw damper engage switch to ON.
(2)
Move yaw damper test switch, on center instrument panel, to the right. Observe yaw damper test meter needle and rudder moves right.
CAUTION: DO NOT ACTUATE TEST SWITCH FOR MORE THAN 10 SECONDS.
(3)
Place yaw damper engage switch off.
(4)
Move yaw damper test switch to the right and left. Observe yaw damper test meter needle and rudder do not move in either direction.
(5)
Remove electrical and hydraulic power if no longer required.
D. Test Rudder Transfer Valve (Aircraft not incorporating SB 27A1206)
(1)
Place yaw damper engage switch to ON.
(2)
Move yaw damper test switch, on center instrument panel, to the right. Observe yaw damper test meter needle moves right, then returns to center. Observe rudder moves approximately 2 degrees right, then returns to center.
CAUTION: DO NOT ACTUATE TEST SWITCH FOR MORE THAN 10 SECONDS.
(3)
Move yaw damper test switch to the left. Observe yaw damper test meter needle moves left, then returns to center. Observe rudder moves approximately 2 degrees left, then returns to center.
(4)
Place yaw damper engage switch off.
(5)
Remove electrical and hydraulic power if no longer required.
E. Test Rudder Solenoid and Transfer Valves (Aircraft incorporating SB 27A1206, Yaw Damper Coupler P/N 10-62253, 4084042)
(1) Perform Yaw Damper Coupler Installation Test (Ref 22-12-01/401).
May 01/00 22-12-21 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MACH TRIM SYSTEM - TROUBLE SHOOTING
1. General
A. The mach trim system can be checked for proper operation by using the mach trim test switch on overhead panel P5 or the self-test switch on the front of the mach trim coupler. (Refer to Mach Trim System - Adjustment/Test.) Failure of the mach trim system, as indicated by the mach trim failure light on overhead panel P5 and the meter and light on the coupler, usually indicates the coupler is faulty. The mach trim failure light will also be illuminated if the coupler self-test switch is left in any position other than OFF. Replacement of the coupler will correct the majority of any faults which may occur. The mach trim system operates with the autopilot system either engaged or not engaged. If no elevator movement results when the mach trim system is operated and the pitch channel is engaged, the neutral shift sensor is faulty (assuming the pitch channel operates normally). Connectors may also be a source of trouble. If replacement of the coupler does not correct the trouble, connectors and wiring should be checked for damage.
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