5. Prepare for Installation
A. Check for allowable wear at elevator feel computer installation linkage attachment points (Ref 27-31-131, Inspection/Check).
B. If input arm (3) is installed on feel computer (4), check that safety pin is installed and secured in input arm (3) and feel computer rigging pin holes (Fig. 401).
WARNING: DO NOT LIFT OR HANDLE FEEL COMPUTER (4) BY INPUT ARM (3). SAFETY PIN MUST BE USED TO RESTRAIN INPUT ARM (3) FROM ROTATION DURING SHIPPING, HANDLING, AND STORAGE. DO NOT APPLY TORQUE EXCEEDING 300 POUND-INCHES TO INPUT ARM (3). DAMAGE MAY OCCUR TO FEEL COMPUTER (4) AFFECTING AUTOPILOT AUTHORITY.
C. If replacement feel computer is being installed, refer to Fig. 401 and install parts from removed computer on replacement computer as follows:
(1)
Lightly lubricate O-rings with Skydrol Assembly Lube MCS 352, then install pneumatic and hydraulic fittings (9) and (16) in feel computer (4).
(2)
Accomplish following checks:
(a)
If replacement computer has input arm (3) installed, check that arm is installed per Fig. 402.
(b)
If replacement computer does not have input arm (3) installed, remove shipping sleeve from end of computer input arm shaft, install input arm (3) on shaft with washer and plug per Fig. 402.
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500 Elevator Feel Computer Input Arm Installation Nov 01/73 Figure 402 27-31-131 Page 404A/404B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(c) Tighten plug within 150 to 200 pound-inches, and install and secure safety pin per par. B.
WARNING: ENSURE THAT INDEX PIN ON SHAFT SPLINE IS LINED UP WITH MISSING TOOTH ON INPUT ARM SPLINE. TIGHTENING PLUG WITH IMPROPERLY ALIGNED INPUT ARM CAN DAMAGE PIN AND SHAFT. WHEN TIGHTENING PLUG, 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.
(3)
Install stabilizer trim potentiometer (15) (Ref Chapter 22, Auto Flight).
CAUTION: IT IS POSSIBLE TO INSTALL POTENTIOMETER CRANK BACKWARD (REVERSED 180 DEGREES). CRANK MUST BE INSTALLED AS SHOWN IN FIG. 401 FOR PROPER AUTO STABILIZER TRIM OPERATION.
(4)
Attach micro-adjustment rod (5) to feel computer output arm (8) and to potentiometer crank. If output arm (8) is not installed, install as required.
(5)
Manually set horizontal stabilizer B dimension at 41.57 + 0.01 inches (Fig. 403).
D. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
E. Check that following circuit breakers on panel P6 are open. Autopilot stabilizer trim servo, stabilizer trim actuator, stabilizer trim control, master dim and autopilot pitch a/c.
F. Remove safety pin and install rigging pin E-3 in input arm (3) and feel computer (4).
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501 Stabilizer Trim Jackscrew Setting
Jun 20/87 Figure 403 27-31-131
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
6. Install Feel Computer
A. Position feel computer (4, Fig. 401) in airplane and install four mounting bolts (15), nuts, and washers.
B. With rigging pin E-4 installed, check that bolt can be easily installed through stabilizer pushrod
(1) and feel computer input arm (3).
C. If bolt does not fit, loosen checknut (2) on stabilizer pushrod and rotate rod end fitting until bolt can be easily installed.
D. Tighten checknut and secure stabilizer pushrod to computer input arm.
E. Check stabilizer pushrod for minimum thread engagement. At least 50% of inspection hole shall be blanked by rod end fitting.
F. Connect stabilizer trim potentiometer return spring (17), to feel computer.
G. Remove rigging pin E-4.
H. Remove caps and plugs from pneumatic ports and lines.
I. Refit two pneumatic pitot lines (13) to feel computer (4).
J. Remove plugs and refit two hydraulic supply pressure lines (10), two return lines (12) and two computer pressure lines (11) to feel computer housing.
CAUTION: ENSURE HYDRAULIC PRESSURE AND RETURN LINES ARE PROPERLY CONNECTED TO THEIR RESPECTIVE PORTS. IMPROPER MATING OF HOUSING.
K. Remove plugs and connect drip tubes (two places) at fittings on feel computer and tighten clamps.
L. Remove caps and install differential pressure switch electrical connector (6) and autopilot potentiometer electrical connector (7).
M. Provide elevator systems A and B hydraulic power (Ref 27-31-0 MP).
N. Move control column fore and aft through full range of travel until movement is smooth and artificial feel is normal to bleed air from system. As air is bled out, artificial feel forces increase.
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