曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

A.  The rudder solenoid and transfer valves are externally mounted on the aft end of the rudder power unit located in the lower area of the vertical fin.
2.  Prepare to Remove Valve
A.  Depressurize hydraulic systems A and B (Ref 29-11-0, and 29-12-0, MP).
WARNING:  PRESSURIZING HYDRAULIC SYSTEMS WILL SUPPLY POWER TO RUDDER, AILERON, ELEVATOR, SPOILER AND SPEED BRAKE SYSTEMS. CARE SHOULD BE TAKEN TO ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.
B.  Open yaw damper circuit breakers on P6 panel.
C.  Remove access panels 9512 and 9514 (Ref Chapter 12, Access Door and Panels).
3.  Remove Valve
A.  Remove mounting bolts and lift valve and seal plate from power unit.
B.  Cover all openings.
4.  Install Valve
A.  Verify seal plate and O-rings are satisfactory, or replace.
B.  Lubricate O-rings with BMS 3-11 fluid and install valve and seal plate on power unit.
C.  Install mounting bolts and tighten to 40-50 pound-inches torque.
D.  Lockwire bolts.
E.  Pressurize hydraulic systems A and B (Ref 29-11-0 and 29-12-0).
F.  Check for leakage and operation of valve (Ref Rudder Solenoid Valve - Adjustment/Test).
G.  Replace access panels.
May 15/81 22-12-21 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

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 - Unpublished Work - See title page for details.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.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 2(70)