(14)
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.
(15)
Remove rigging pins E2 and E3, and install shoulder bolt and nut in each quadrant so that bolt head is facing outboard.
(16)
Remove rigging pins E1 and E5 from quadrants.
(17)
Cycle control column several times gradually decreasing to zero.
(18)
Position test box SELECT switch to CAPT and record voltage. Position test box SELECT switch to F/O and record voltage. The voltages must be less than 350 mv.
(19)
Check that difference between CAPT and F/O voltages does not exceed 150 mv.
NOTE: If voltage is excessive, check control quadrant and bearings for structural interference, excess friction in support bearings or links and/or misalignment of links.
(20)
Turn off test box and reconnect force transducers to airplane wiring.
(21)
Close access door.
(22)
Test pitch control wheel steering force transducer.
3. Pitch Force Transducer Test
A. Equipment and Materials
(1) Spring Scale - 0 to 50 pounds, John Chatillon and Sons, Model DPP-50
500
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-91 Page 505
B. Prepare to Test Pitch 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 systems A and B (Ref 29-11-0 MP and 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.
(4)
Ensure elevators are operable.
(5)
Ensure autopilot, vertical gyro, and air data computer circuit breakers are closed.
C. Test Pitch Force Transducers
(1)
Place autopilot system select switch on A or B.
(2)
Connect spring scale to center hub of captain's control column.
(3)
Engage pitch channel.
NOTE: If the force transducers are not adjusted properly, the pitch channel may not engage.
(4)
Slowly push on the captain's column until the column starts to drive. It should require 3.8 to 7.5 pounds. Record value.
(5)
Repeat step (4) except pull on column. The recorded values should differ by less than 2 pounds.
(6)
Repeat steps (2) thru (5) for first officer's column. Position pitch mode select switch to ALT HOLD.
(7)
Repeat steps (2) thru (6) except apply a steady pull on the control column until the pitch mode select switch returns to the OFF position. The pull required should be greater than 15 and less than 23 pounds.
D. Restore Airplane to Normal Configuration
(1)
Remove spring scale from control wheel.
(2)
Disengage pitch channel.
(3)
Remove electrical and hydraulic power from airplane if no longer required.
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22-11-91 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/93
PITCH CONTROL WHEEL STEERING FORCE TRANSDUCER -REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on WA N235WA-N259WA GJ B-2509 and B-2510
1. General (Fig. 401)
A. Each control column has a pitch force transducer installed on the elevator control quadrant assembly. The two force transducers are installed opposite to each other; however, removal/installation of the transducers is similar.
2. Equipment and Materials
A. Rigging Pins E1 and E5 - 0.309 (+0.003/-0.000)-inch diameter, 6-inch minimum length (MS20392-4)
3. Remove Pitch Force Transducer
A. Open autopilot circuit breakers on P6 panel.
B. Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
C. Disconnect force transducer connectors from airplane wiring (Fig. 401).
D. Remove force transducer cable from clamps.
E. Remove bolts, washers, and nuts from force transducer and quadrant assembly; remove transducer.
4. Prepare to Install Pitch Force Transducer
A. Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
B. Remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).
C. Insert rigging pin E5 in elevator right aft quadrant (Fig. 402).
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