(3)
Place yaw damper engage switch to 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.
D. Test Rudder Solenoid Valve (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 01/01 22-11-61 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER TRANSFER VALVE - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The rudder transfer valve is externally mounted on the forward end of rudder power unit located in the lower area of the vertical fin (Fig. 401).
2. Prepare to Remove Transfer 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 Doors and Panels).
3. Remove Transfer Valve
A. Remove mounting bolts and lift valve and seal plate from power unit (Fig. 401).
B. Cover all openings.
4. Install Transfer 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 (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 Transfer Valve -A/T).
G. Replace access panels.
Jun 20/85 22-11-71 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
