ELEVATOR FEEL COMPUTER - REMOVAL/INSTALLATION
1.  General
A.  The elevator feel computer should be removed from the airplane to replace the differential pressure switch or any other computer components requiring replacement. Refer to Chapter 22, Auto Flight for Autopilot Potentiometer Maintenance Practices.
2.  Equipment and Materials
A.  Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO.  F70207-( )  DIAMETER (INCHES)  LENGTH (INCHES)  FUNCTION 
E-4  -11  0.309-0.311  6.7±0.25  FEEL COMPUTER INPUT ARM 

B.  Trammel Bar - F80055-1
C.  Skydrol Assembly Lube - MCS 352 (20-30-21)
D.  Elevator Feel Computer Safety Pin - F80153-1
E.  Air Pressure Regulator - F72928-53 (Preferred), or -52 (Optional)
3.  Prepare for Removal
A.  Remove elevator systems A and B hydraulic power (AMM 27-31-0/201).
B.  Open aft compartment access door 3701.
C.  Position horizontal stabilizer at B dimension of 41.57 +0.01 inches (Fig. 403).
D.  Open following circuit breakers on panel P6: Autopilot stabilizer trim servo, stabilizer trim actuator, stabilizer trim control, master dim, autopilot pitch a/c.
E.  Install and secure safety pin in input arm (3, Fig. 401) and feel computer (4).
WARNING:  SAFETY PIN MUST BE INSTALLED IN FEEL COMPUTER (4) RIGGING PIN HOLES TO RESTRAIN INPUT ARM (3) FROM ROTATION DURING HANDLING, SHIPPING AND STORAGE. DO NOT LIFT COMPUTER (4) BY INPUT ARM (3). DO NOT APPLY TORQUE EXCEEDING 300 POUND-INCHES TO INPUT ARM (3). DAMAGE MAY OCCUR TO COMPUTER (4) AFFECTING AUTOPILOT AUTHORITY.
4.  Remove Feel Computer (Fig. 401)
A.  Disconnect stabilizer trim potentiometer return spring (17), from feel computer (4).
538 
May 01/00  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-131 Page 401 

G10129G10248
Elevator Feel Computer Installation  538 
27-31-131  Figure 401 (Sheet 1)  Oct 20/84 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

538  Elevator Feel Computer Installation 
Nov 01/73  Figure 401 (Sheet 2)  27-31-131 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

B.  Remove bolt attaching stabilizer pushrod (1) to input arm (3).
C.  Discount differential pressure switch electrical connector (6) and autopilot potentiometer electrical connector (7) and install caps.
D.  Release two pneumatic pitot lines (13) from feel computer (4) and install plugs.
E.  Release two hydraulic supply pressure lines (10), two return lines (12) and two computer pressure lines (11) from feel computer (4) and install plugs.
CAUTION:  WHEN DISCONNECTING HYDRAULIC PRESSURE ON RETURN LINE, RELEASE CONNECTION SLOWLY AND ALLOW SYSTEM PRESSURE TO DROP BEFORE COMPLETELY REMOVING LINE. BE PREPARED TO CATCH SPILLED HYDRAULIC FLUID. 
F.  Release drip tubes (2 places) from fittings on feel computer.
G.  Cap and plug all open ports, hydraulic lines and pneumatic lines.
H.  Release four computer mounting bolts (14), and remove feel computer from airplane.
I.  If replacement computer is to be installed, perform the following steps on removed feel computer:
(1)  
If replacement computer does not have input arm (3) installed, remove input arm (3) from shaft on old computer and retain for subsequent installation.

WARNING:  IF INPUT ARM (3) CANNOT BE EASILY REMOVED, DO NOT ATTEMPT REMOVAL WITH TOOLS. INTERNAL SHEAR PINS MAY BE SHEARED BY ATTEMPTING TO REMOVE IMPROPERLY ALIGNED INPUT ARM (3), WHEN REMOVING PLUG FROM COMPUTER ARM (3), HOLD COMPUTER ARM (3) AGAINST TORQUE APPLIED TO PLUG. DO NOT ALLOW TORQUE APPLIED TO PLUG TO REACT AGAINST INTERNAL STOPS. DAMAGE MAY OCCUR TO COMPUTER (4) AFFECTING AUTOPILOT AUTHORITY.

(2)  
Detach micro-adjustment rod (5) from computer output arm (8) and potentiometer crank. If required, remove output arm (8).

(3)  
Remove stabilizer trim potentiometer (15) (Ref Chapter 22, Auto Flight).

(4)  
Remove pneumatic and hydraulic fittings (9) and (16) from computer housing. Install shipping plugs in open ports.

NOTE: Shipping plugs may be obtained from replacement computer.
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27-31-131 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/79 
　
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