(a)
On the forward support link, measure the length of the eyebolt thread extension above the adjustable nuts.
(b)
On the aft support link, measure the length of the two eyebolts thread extension below the adjustable nuts.
(c)
Make sure that the three thread extensions are the same within 0.12 inch.
(2)
Measure dimension A.
I. Check that A dimension of support link assemblies are equal to within +0.06 inch of each other (measure at 3 places) to ensure proper alignment of forward mechanism (Fig. 401).
NOTE: Measurement is taken from center of aft support bolts and threaded stud on aft support link assembly (right and left side) and center to center of forward support link mounting bolts and bolt through lower end of eyebolt.
J. Attach STA cable eye in slot in bottom of drum.
CAUTION: TO PRECLUDE CRACKING DRUM FLANGES, DO NOT TIGHTEN NUT MORE THAN 60 POUND-INCHES.
K. Rotate stabilizer trim control wheel to wind STA cable 28-1/2 turns on front drum. Hold STB cable taut as it winds on rear drum as STA cable winds on front drum.
L. Wind STB cable approximately 4-1/2 turns on front drum and attach.
CAUTION: TO PRECLUDE CRACKING DRUM FLANGES, DO NOT TIGHTEN NUT MORE THAN 60 POUND-INCHES.
NOTE: A 50-pound load may be applied to the stabilizer trim control wheel to stretch STA cable to facilitate attachment of STB cable.
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Oct 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-41 Page 405
M. Loosen chain by adjusting support link assembly eyebolts.
N. Adjust cable to specified tension with turnbuckle (7). See Fig. 402 for cable tension loads.
CAUTION: CABLE TENSION MUST BE ADJUSTED BEFORE FINAL ADJUSTMENT OF CHAIN.
O. Repeat steps G. and H.
P. Close stabilizer trim actuator and autopilot stabilizer trim servo circuit breakers on panel P6.
Q. Rotate stabilizer to full travel in both directions and then center cables on drum. Check that system operates freely and without binding in either direction through full travel.
R. Check that cable tension is within limits specified in Fig. 402. If tension is not within limits, repeat steps G., H., and M.
S. Set stabilizer B dimension at 41.57 +0.05 inches (Fig. 402).
T. Check each end of core of flexible shaft for visible lubrication.
U. Rotate flexible drive shaft until stabilizer trim indicators align with 3 +1/4 stabilizer trim units on control stand metal-cal.
V. Insert flexible drive shaft into drum shaft in forward mechanism. Check for positive engagement of splines on shaft before tightening union.
W. Install drip shield on bottom of gear housing (not on all airplanes).
X. Make sure that the clearance between the chain and the adjacent wire bundles is as follows:
CAUTION: IF YOU DO NOT KEEP SUFFICIENT CLEARANCE, WIRES CAN BE DAMAGED.
(1)
The lateral clearance must be not less than 0.5 inch.
(2)
The vertical clearance (measured parallel to the chain) must be not less than 1.5 inches.
Y. Remove electrical power, if no longer required.
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G42423
500 Stabilizer Cable Tension and Trim Jackscrew Setting
Feb 20/90 Figure 402 27-41-41
Page 407
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STABILIZER TRIM BRAKE - REMOVAL/INSTALLATION
1. Equipment and Material
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-1 ST-2 -11 -16 0.309-0.311 0.182-0.186 6.7 ±0.25 2.7 ±0.25 FWD Control Quadrant Stabilizer Trim Brake Arm
B. Corrosion Preventive Compound - MIL-C-16173, Grade 2 (Ref 20-30-21)
C. Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
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