ELEVATOR TRANSFER VALVE -ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. Elevator Transfer Valve Test
A. General
(1) This test ensures that the elevator transfer valve operates properly and assumes that the rest of the autopilot is operating normally.
B. Prepare to Test Elevator Transfer Valve
(1)
Pressurize hydraulic systems A and B (Ref 29-11-0, Hydraulic System A - Maintenance Practices and 29-12-0, Hydraulic System B - Maintenance Practices).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(2)
Assure that all autopilot and associated circuit breakers are closed.
(3)
Place autopilot system select switch to appropriate position.
C. Test Elevator Transfer Valve
(1)
Engage autopilot.
(2)
Push, then pull, then center control column. Note increase in pressure required to move control column and check that elevator moves down, then up and returns to center with control column. Observe that autopilot does not disengage.
(3)
Disengage autopilot and check that control column/wheel moves easily with less pressure required than with autopilot engaged.
(4)
Remove electrical and hydraulic power if no longer required.
5C8
Jun 20/85 22-11-41 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER SOLENOID VALVE - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The rudder solenoid valve is externally mounted on the aft end of rudder power unit located in the lower area of the vertical fin (Fig. 401).
2. Prepare to Remove Solenoid 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. Remove access panels 9512 and 9514 (Ref Chapter 12, Access Door and Panels).
3. Remove Solenoid Valve
A. Remove mounting bolts and lift valve and seal plate from power unit (Fig. 401).
B. Cover all openings.
4. Install Solenoid Valve
NOTE: Do not install rudder solenoid valves with these part numbers:
Boeing P/N 10-60811-1, or -9
Boeing P/N 10-60811-3 with Parker P/N 59600-5007
Refer to the IPC for correct parts usage.
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 (Fig. 401).
C. Install mounting bolts and tighten to 40-50 pound-inches torque.
D. Lockwire bolts.
E. Pressurize hydraulic system B (Ref 29-12-0).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
F. Check for leakage and operation of valve (Ref Rudder Solenoid Valve -A/T).
G. Replace access panels.
May 01/99 22-11-61 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H19199
Rudder Solenoid Valve Installation 545
22-11-61Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 01/74
RUDDER SOLENOID VALVE - ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. Rudder Solenoid Valve Test
A. General
(1) This test ensures that the solenoid valve operates properly and assumes that the rest of the yaw damper system is operating normally.
B. Prepare to Test Rudder Solenoid Valve
(1)
Pressurize hydraulic system B (Ref 29-12-0 MP).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(2)
Close appropriate circuit breakers.
C. Test Rudder Solenoid Valve (Aircraft not incorporating SB 27A1206)
(1)
Place yaw damper engage switch to ON.
(2)
Move the yaw damper test switch, located on center instrument panel, to the right. Observe yaw damper test meter needle and rudder moves to the right.
CAUTION: DO NOT ACTUATE TEST SWITCH FOR MORE THAN 10 SECONDS. 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 1(112)
