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.
B. Test Aileron Position Transducer
(1)
Engage 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.
C. Restore Airplane to Normal Configuration
(1)
Disengage autopilot engage switch.
(2)
Determine whether there is any further need for electrical power on the airplane; if not, remove external power.
5C8
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR POSITION TRANSDUCER - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. An elevator position transducer is externally mounted between ends of clevis on upper end of B elevator power unit and may be installed but not used on A power control unit.
B. This procedure covers transformer portion of transducer only. Detail disassembly of the power unit is required to remove the transducer rod (Fig. 401).
2. Equipment and Materials
A. Rigging Pin - 0.309 +0.003/-0.000-inch diameter (MS20392-4)
B. Grease - MIL-G-23827
3. Prepare to Remove Transducer Transformer
A. Depressurize hydraulic system A and B (Ref 29-11-0, Maintenance Practices and 29-12-0, Maintenance Practices).
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 panel 3802 for both left and right elevator power units (Ref Chapter 12, Access Doors and Panels).
C. Install rigging pin in aft control quadrant (Fig. 401).
4. Remove Transducer Transformer
A. Remove power control unit upper mounting bolt from output torque tube. (See figure 401.)
B. Remove transducer mounting bolts and lift transducer from power unit.
D. Cover all openings.
5. Install Transducer Transformer
A. Verify O-ring is satisfactory or replace.
B. Install transducer transformer. (See figure 401.)
May 20/82 22-11-241 Page 401
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H29037
Elevator Position Transducer Installation 500
22-11-241Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/67
C. Install transducer mounting bolts and tighten to 40-50 pound-inches.
D. Lockwire bolts.
E. Apply grease to entire shank of mounting bolt and install power control unit upper mounting bolt.
F. Remove rigging pin from control quadrant.
G. 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.
H. Check for hydraulic leakage and operation of transducer (Ref Elevator Position Transducer -Adjustment/Test).
I. Replace access panel.
551
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ELEVATOR POSITION TRANSDUCER - ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. Elevator Position Transducer Test
A. Prepare to Test Elevator Position Transducer
(1)
Verify control surfaces are free to move.
(2)
Provide ground power to the airplane and energize buses on load control center P6.
(3)
Ensure autopilot circuit breakers, located on load control center P6, are closed.
(4)
Pressurize hydraulic systems A and B (Ref 29-11-0, 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
B. Test Elevator Position Transducer
(1)
Engage autopilot.
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