(2)  
Adapter cables (2 required) F80218-48

(3)  
Rigging Pins E1 and E5 - 0.309 +0.003/-0.0-inch diameter, 6.0-inch minimum length (MS20392-4)

(4)  
Rigging pins E2 and E3 (2) - 0.4941 士0.0004-inch diameter, 1.5-inch minimum length

(5)  
VTVM - Hewlett Packard Model 410C

B.  Prepare for Adjustment
(1)  
Provide electrical power to the airplane and energize load control center P6.

(2)  
Ensure elevators are properly rigged (Ref Chapter 27 Elevator and Tab Control System).

(3)  
Open pitch channel circuit breakers on load control center P6.

(4)  
Open lower nose access door 1103 and tail cone access door 3802 (Ref Chapter 12 Access Doors and Panels).

Feb 20/93 22-11-91 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

C.  Adjust Pitch Force Transducer (Fig. 501)
(1)  
Install rigging pin E1 in forward left control quadrant and rigging pin E5 in right aft control quadrant (Fig. 502).

NOTE:  Rigging pins should fit freely.

(2)  
Disconnect both force transducer cable connectors from airplane wiring.

(3)  
Remove bolt, washer, and nut from adjustable end of force transducers.

(4)  
Remove shoulder bolt from each quadrant assembly and install rigging pins E2 and E3.

NOTE:  Rigging pin locations are labeled on quadrant assembly. If cables are rigged properly, the rigging pins should be easily installed.

(5)  
Connect captain's force transducer to the captain's connector on the test box with adapter cable.

(6)  
Connect first officer's force transducer to the first officer's connector on the test box with adapter cable.

(7)  
Energize test box and allow force transducers to warm up and stabilize for 15 minutes.

CAUTION:  USE ONLY 115 VOLTS, 400 Hz AC. USE OF 60 Hz VOLTAGE WILL DAMAGE TRANSDUCERS.

(8)  
Position the SYSTEM A - SYSTEM B switch in the SYSTEM A position.

(9)  
Position test box SELECT switch to CAPT. Measure and record output voltage at static conditions. The output should be no more than 80 mv. Check electrical cable installation to see if null can be lowered by loosening cable a small amount. Tighten cable clamps.

NOTE:  Hold transducer level to minimize error in reading. The fine and coarse adjustments should be checked for some threads showing.

(10)
Position test box SELECT switch to F/O. Measure and record output voltage at static conditions. The output should be no more than 80 mv.

(11)
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. Install bolt, washer, and nut. 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. Install bolt, washer, and nut.

NOTE:  Coarse adjustment is approximately 0.016 inch per turn. Fine adjustment is approximately 0.006 inch per turn.
500 
22-11-91 Page 502  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/93 

G42317
500  Pitch Force Transducer Adjustment 
Feb 20/93  Figure 501  22-11-91 
Page 503 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Pitch Transducer Rigging Pin Location  500 
22-11-91  Figure 502  Feb 20/93 
Page 504 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(12)
Adjust fine adjustment until voltage obtained for each force transducer is within ± 20 mv of the values measured in steps (9) and (10). To ensure transducer is not prE1oaded, turn coarse adjustment until mounting hole is parallel with mounting hole at opposite end of transducer after each fine adjustment and before taking reading.

NOTE:  Use the CAPT and F/O positions on the test box. More than one null may be obtained.

(13)
Position test box SELECT switch to TOTAL. The indicated voltage should be greater than either individual force transducer null voltage. If the indicated voltage is less than either individual force transducer null voltage, the transducers are not nulled correctly. Position test box SELECT switch to CAPT or F/O and readjust the corresponding force transducer to obtain a new null and then check voltage with test box switch in TOTAL position. Repeat as necessary until an acceptable voltage is obtained.
　
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