(3)
For A/P aileron actuator valves, rotate control wheel left, then right, then center control wheel. Note increase in pressure required to move control wheel and check that left aileron moves up, then down then returns to center with control wheel. Observe that autopilot does not disengage.
(4)
Disengage autopilot and check that control column/wheel moves easily with less pressure required than with autopilot engaged.
(5)
Remove electrical and hydraulic power if no longer required.
May 20/82 22-11-12 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON TRANSFER VALVE - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. An aileron transfer (servo) valve is externally mounted on right end of B aileron power unit and may be installed, but not used on A aileron power unit (Fig. 401).
2. Remove Transfer Valve
A. Depressurize aileron 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 mounting bolts and lift valve and seal plate from power unit (Fig. 401).
C. Cover all openings.
3. 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 Aileron Transfer Valve -Adjustment/Test).
Jun 20/85 22-11-21 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H28644
Aileron Transfer Valve Installation 500
22-11-21Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/67
AILERON TRANSFER VALVE -ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. Aileron Transfer Valve Test
A. General
(1) This test ensures that the aileron transfer valve operates properly and assumes that the rest of the autopilot is operating normally.
B. Prepare to Test Aileron Transfer Valve
(1)
Pressurize hydraulic system B (Ref 29-12-0, 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.
C. Test Aileron Transfer Valve
(1)
Engage autopilot AIL engage switch.
(2)
Rotate control wheel left, then right, then center control wheel. Note increase in pressure required to move control wheel and check that left aileron moves up, then down then returns to center with control wheel. 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 22-11-21 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR SOLENOID VALVE - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. An elevator solenoid valve is externally mounted on lower end of B elevator power unit and may be installed, but not used on A elevator power unit (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.
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