E. Access
 (1)  
Location Zones
 211/212 Control Cabin
 311/312 Area Aft of Pressure Bulkhead to BS 1787.45
 313/314 Stabilizer Center Section Compartment

 (2)  
Access Panels
 311AL Forward Stabilizer Compartment
 313AL Elevator Feel Unit

 F.
Install the Feel Unit (Fig. 202)

 S 432-021
 (1)  
Install the bolts (21, 25), washers (22, 26) and nuts (23, 27) that attach the feel unit (5) to the support bracket (24).

 S 432-022

 (2)  
Install the bolt (30), washer (31), and nut (32) to connect the arm assembly (29) to the feel unit (5).

 S 432-023

 (3)  
Remove the plugs from the hydraulic lines and the caps from the ports.

 S 432-024

 (4)  
Connect the hydraulic lines (6, 7, 8, 9) to the feel actuator (10). (AMM 20-10-09/401)

 S 432-025

 (5)  
Install the nuts (13), washers (14), and bolts (15) to connect the control rods on the neutral shift mechanism (1) to the feel unit (5) (2 locations).

 NOTE: If the adjustable rod is not in the tolerance limits, you
____ must do the adjustment for the adjustable rod (Ref 27-31-00).
 S 432-026
 (6)  
Install the bolts (16), washers (17, 19) and nuts (18, 20) to connect the control rods on the aft quadrant (12) to the feel unit (5) (2 locations).

 (a)  
Tighten the nuts as follows: 1) Tighten the nut (18) to 50-60 pound-inches (5.7-6.7 Nm) 2) Tighten the nut (20) to 10 pound-inches (1.1 Nm).

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 S 432-027
 CAUTION:_______DO NOT REPLACE THE DECENTERING SPRINGS ONE AT A TIME. ALL FOUR OF THE DECENTERING SPRINGS MUST BE CLOSE TOLERANCE SPRINGS (| 2 PERCENT). DAMAGE TO THE AIRPLANE CAN OCCUR IF THEY ARE NOT CLOSE TOLERANCE SPRINGS.
 (7)  
Use the spring removal/installation tool to install the decentering springs (11) on the feel unit (5) (Fig. 204).

 S 212-028

 (8)  
Make sure the springs are installed correctly.

 S 432-029

 (9)  
Connect the electrical connectors to the RVDTs (3 locations).

 S 822-030

 (10)
 Do the adjustment for the mechanical linkages for the feel and centering unit (Ref 27-31-00) (Fig. 203).

 NOTE: You must do the adjustments for the neutral shift
____ transducers, autopilot servo rods, and PCA input control rods after you adjust the mechanical linkages for the feel and centering unit (Ref 27-31-00).
 S 712-031
 (11)
 Do the test for the elevator feel system forces (Ref 27-31-00).

 S 732-066

 (12)
 Do the Control Column Breakout Test in the Elevator Control System -System Test (AMM 27-31-00/501).

 S 732-067

 (13)
 Do the Autopilot Hardover Test in the Elevator Control System -System Test (AMM 27-31-00/501).

 S 732-068

 (14)
 Do the MCDP Ground Test 68 - Elevator Servo Limit (FIM
 22-00-04/101).

 G.
Put the Airplane Back to Its Usual Condition

 S 862-032
 (1)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:

 (a)  
AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND; 11B19, STAB TRIM ALT

 (b)  
11C12, STAB TRIM SHUTOFF LEFT

 (c)  
11C13, STAB TRIM SHUTOFF RIGHT

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757 MAINTENANCE MANUAL
 (d)  
11H11 or 11C05, STAB TRIM CONT L

 (e)  
11H17, FLT CONT SHUTOFF TAIL LEFT

 (f)  
11H18, FLT CONT SHUTOFF TAIL CTR

 (g)  
11H20, STAB TRIM CONT R
　
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