B. Prepare for Adjustment
(1)
Provide electrical power to the airplane and energize load control center P6.
(2)
Pressurize hydraulic system B (Ref 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.
(3)
Ensure hydraulic power is applied to both aileron power control units.
(4)
Rotate control wheel士30 degrees and gradually center control wheel. Tag control wheel indicating it should not be moved.
NOTE: Power control units must be operative to ensure cables are aligned properly in relation to force transducer.
(5)
Remove system B hydraulic power (Ref 29-11-0).
(6)
Open roll channel circuit breakers on load control center P6.
(7)
Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
C. Adjust Roll Force Transducer
(1) Disconnect force transducer cable connector from airplane wiring (Fig. 501).
Feb 20/93 22-11-111 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2)
Insert shims between shaft and drum. Gap settings should be 0.021 +0.003/-0.0 inch (View 1, Fig. 502).
(3)
Remove bolt from adjustable end of force transducer.
(4)
Connect force transducer to captain's connector with adapter cable and energize test box. Allow transducer to warm up and stabilize for 15 minutes.
CAUTION: USE ONLY 115 VOLTS, 400 HZ AC. USE OF 60 HZ VOLTAGE MAY DAMAGE TRANSDUCER.
(5)
Position the SYSTEM A - SYSTEM B switch in the SYSTEM A position.
(6)
Position test box SELECT switch to CAPT and measure output voltage at static conditions. The output should not exceed 80 mv. If the null is higher, refer to removal/installation then loosen electrical cable to determine if null can be lowered by an adjustment to the cable installation. Tighten cable clamps.
NOTE: The fine and coarse adjustments should be checked for some threads showing.
(7)
On airplanes with Sperry force transducers, remove lockwire on collar clamp, loosen lockscrew and adjust rod end (coarse adjustment) on each force transducer until mounting bolt can be easily inserted. Insert bolt. On airplanes with Kavlico force transducers, remove lockwire, loosen locknut on adjustable rod end, loosen locknut on adjustable sleeve and adjust rod end (coarse adjustment) on each force transducer until mounting bolt can be easily inserted. Insert bolt.
NOTE: Coarse adjustment is approximately 0.016 inch per turn. Fine adjustment is approximately 0.006 inch per turn.
(8)
Measure force transducer null voltage after installation and rotate fine adjustment nut until previous null + 10 mv is obtained.
(9)
On airplanes with Sperry force transducers, tighten lockscrew on collar clamp and install lockwiring. On airplanes with Kavlico force transducers, tighten locknut on adjustable sleeve (pressing washer against end cap of transducer), tighten locknut on rod end and install lockwiring.
(10)
Remove shims.
(11)
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.
(12)
Cycle control wheel + 30 degrees. Gradually center control wheel.
(13)
Measure null voltage. Check that null voltage is less than 150 mv.
551
22-11-111 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/93
G42404
500 Roll Force Transducer Adjustment
Feb 20/93 Figure 501 22-11-111
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(14)
Turn off test box and reconnect force transducer to airplane wiring.
(15)
Close access panel.
(16)
Remove control column tag and test roll control wheel force transducer.
3. Roll Force Transducer Test
A. Equipment and Materials
(1) Adapter Assembly, Control Wheel Torque Tool – F72867-1
B. Prepare to Test Roll Force Transducer
(1)
Verify control surfaces are free of obstructions and personnel.
(2)
Provide electrical power to the airplane and energize load control center P6.
(3)
Pressurize hydraulic system B (Ref 29-12-0).
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