(3)  
Check to ensure right elevator trailing edge is in line with tail cone index +0.06 inch.

(4)  
Remove VTVM and connect VTVM to J7A and J8A (NSS FEEDBACK) on test set. Check that sensor voltage is 1.348 +0.5 volts.

NOTE:  When facing sensor, index mark on sensor housing should appear rotated clockwise approximately 9 degrees against index mark on sensor shaft.

(5)  
If voltage within limits, proceed to step (7). If voltage out of limits refer to Elevator Neutral Shift Sensor - Removal/Installation, and perform installation procedure 3.A thru 3.I.

(6)  
Repeat adjustment steps D.(1) thru D.(4) to obtain voltage within 1.348 +0.5 volts.

(7)  
Remove lockwiring and turn thumb nut on microadjustment rod until 1.348 +0.03 volts is obtained.

(8)  
Using horizontal stabilizer trim wheel, drive stabilizer leading edge down and verify that voltage decreases (this ensures that sensor is set to correct side of null). If not correct, repeat steps (5) thru (7) until correct null is obtained.

(9)  
Lockwire thumb nut on microadjustment rod.

580 
22-11-122 Page 502  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/84 

E.  Restore Airplane to Normal
(1) 
 Disconnect VTVM.

(2)  
Remove test cable and reconnect sensor connectors to airplane wiring.

(3)  
Remove test set cables and reconnect D1681 to A/P actuator A and D1687 to A/P actuator B.

(4)  
Remove test set power cable.

(5)  
Install tail cone access panel.

(6)  
Remove electrical and hydraulic power if no longer required.

580 
Jun 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-11-122 Page 503 

AILERON FORCE LIMITER - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SBL thru ZS-SBR SD ST-AFK, ST-AFL WA N4502W-N4571M GJ ALL EXCEPT B-2509 and B-2510
1.  General
A.  The aileron force limiter is located at the bottom of the captain's control column on the aileron drum shaft assembly (Fig. 401).
2.  Remove Aileron Force Limiter
A.  Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
B.  Disconnect force limiter electrical connector.
C.  Placing palm of hand underneath force limiter, remove three bolts, washers and nuts, and remove force limiter.
3.  Install Aileron Force Limiter
A.  Grasping force limiter firmly, mate spline with shaft assembly and align three holes in force limiter fitting with holes in shaft assembly bracket.
NOTE: Ensure that smaller diameter of force limiter is facing towards nose of airplane.
B.  Install bolt and washer in forward hole of limiter and bracket and two bolts, washers and nuts in rear holes (rear bolt shafts point down). Tighten bolts.
C.  Connect electrical connector to force limiter.
D.  Check operation of force limiter (Ref Aileron Force Limiter - Adjustment/Test).
E.  Close access doors.
May 15/81 22-11-131 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

H29043
Aileron Force Limiter Installation  501 
22-11-131Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/69 

AILERON FORCE LIMITER - ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1.  Aileron Force Limiter Test
A.  General
(1)  This test ensures that the aileron force limiter operates properly and assumes that the rest of the autopilot system is operating normally.
B.  Prepare to Test Aileron Force Limiter
(1)  
Provide electrical power to the airplane and energize load control center P6.

(2)  
Pressurize hydraulic system A or B (Ref 29-11-0, Maintenance Practices and 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.

(3)  
Ensure that all autopilot, vertical gyro, compass system and air data computer circuit breakers are closed.

C.  Test Aileron Force Limiter
(1)  
Engage autopilot AIL engage switch.

(2)  
Center heading bug on the pilot's HSI and engage heading select mode.

(3)  
Rotate heading bug 45 degrees to the left.

(4)  
On airplanes certified to 35,000 feet altitude (equipped with force limiter part number RM1053M1, RM1053M2, RM1053M2-1), observe that the control wheel rotates CCW and stops between 24 and 28 degrees. On airplanes certified to 37,000 feet altitude (equipped with force limiter part  numbers 10050-4, R1053M17 or R1053M17-1), observe that control wheel rotates CCW and stops between 15 and 19 degrees.
　
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