G11076
Aileron Centering Spring and Trim Mechanism Installation 580
27-11-81 Figure 401 Feb 20/84
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H. Disconnect autopilot aileron position sensor rod and autopilot actuator rod from power control shaft upper input lever by removing nuts, washers, and bolts.
I. Disconnect upper and lower reaction support assemblies from bulkhead by removing nuts, washers, and bolts.
J. Carefully slide centering spring and trim gearbox downward to disengage assembly from trim shaft and aileron power control shaft and remove assembly.
K. Disconnect trim gearbox control rod from centering spring mechanism by removing cotter pin, nut, washer, and bolt.
L. Remove trim gearbox from centering spring mechanism by removing nuts, washers, and bolts.
4. Install Aileron Centering Spring and Trim Mechanism (Fig. 401)
A. Check aileron centering spring and trim mechanism for wear (Ref. 27-11-81 I/C).
B. Check aileron trim gearbox for wear (Ref. 27-11-141 I/C).
C. Install centering spring and trim gearbox as follows:
(1)
Attach trim gearbox to centering spring mechanism bracket with bolts, washers, and nuts.
(2)
Attach control rod to centering spring mechanism with bolt, washer, nut, and cotter pin.
NOTE: If BACB3ONF4-15 bolt is used, also use AN960PD416 washer under head of bolt.
(a)
Ensure that cotter pin does not extend beyond end of bolt.
(b)
Check for clearance between bottom of bolt and support fitting.
(3)
Lubricate trim shaft with grease or corrosion preventive compound.
(4)
Position centering spring and trim gearbox to engage aileron power control shaft and trim shaft simultaneously.
(5)
Install bolts to secure aileron control quadrant shaft to power control shaft. Tighten nuts 30 to 35 pound-inches.
NOTE: If power control shaft does not contain bolt holes, drill holes 0.250 + 0.004/-0.000 inch diameter in power control shaft using holes in quadrant shaft as a guide.
(6)
Secure upper and lower reaction support assemblies to bulkhead by installing bolts, washers, and nuts.
(7)
Pre SB 27-1207; Connect upper and lower input rods to lever assemblies by installing bolt assemblies, washers, and nuts. Tighten large nuts 65 to 90 pound-inches. Tighten small nuts 12 to 15 pound-inches. Check that valve lever on each power control unit is centered between stops (Detail B, Fig. 401). If necessary, adjust input rods (Ref 27-11-0 A/T).
(8)
Post SB 27-1207; Connect upper and lower input rods to lever assemblies by installing bolt assemblies, washers, and nuts. Tighten inner nut to 45-60 pound-inches. Tighten outer nut 12 to 15 pound-inches. Check that valve lever on each power control unit is centered between stops (Detail B, Fig. 401). If necessary, adjust input rods (Ref 27-11-0 A/T).
NOTE: After tightening outer nut, do not retighten inner nut.
(9)
Connect autopilot aileron position sensor rod and autopilot actuator rod to power control shaft upper input lever with nuts, washers, and bolts.
CAUTION: ENSURE THAT AUTOPILOT AILERON POSITION SENSOR ROD IS CORRECTLY ORIENTED AS SHOWN IN 22-11-291. INCORRECT ROD ORIENTATION COULD CAUSE AUTOPILOT COMMANDED TURN WHEN AUTOPILOT IS ENGAGED.
(10)
Connect upper and lower reaction links to reaction support assemblies by installing bolt assemblies, washers, nuts, and cotter pins. Tighten large nuts 300 to 350 pound-inches. Tighten small nuts 170 to 200 pound-inches.
(11)
Check that dimension at trim shaft splined connection is per detail A. If not refer to 27-11-131, R/I for shaft replacement.
502
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-81 Page 403
C. Check that rigging pin A/S-13 passes freely through both walls of aileron trim mechanism. If rigging pin cannot be inserted freely accomplish the following steps:
(1)
Disconnect coupler from trim shaft.
(2)
Rotate trim shaft to permit insertion of rigging pin A/S-13.
(3)
Reconnect trim shaft and coupler.
(4)
Remove rigging pin A/S-13.
D. Remove rigging pin A/S-4.
E. Test centering spring and trim mechanism installation (Ref 27-11-81, A/T).
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