500 Aileron Installation
Aug 01/94 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-11 Page 403
G. Secure hinge bolts with washer and nut at hinge locations 2, 3, and 4.
H. Tighten nut 10 to 20 pound-inches.
I. Install cotter pins at hinge bolt locations 2, 3, and 4.
J. Install hinge bolt with washer under bolt head at hinge location 1. Position bolt head as shown in Fig. 401.
K. Secure hinge bolt with washer and nut at hinge location 1 and tighten 100 to 140 pound-inches.
L. Install cotter pin at hinge bolt location 1.
M. Lift aileron to align aft balance panel hinge, install hinge pin and hinge pin retainer (Fig. 401).
N. Install balance panel hinge seal, retaining strip, and bolts.
G03483
Aileron Balance Panels and Seals 500
27-11-11Page 404 Figure 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/83
O. Connect tab pushrods (Fig. 401) to hinge fitting by installing two attach bolts, washers and nuts.
P. Connect bonding jumpers in a manner to avoid interference with moving parts with the steps that follow:
(1)
Clean surface to give electrical bonding.
(2)
Fillet seal fastener and bonding jumper end with sealant.
(3)
Apply primer plus enamel to exposed bare metal not covered by faying surface.
(4)
Make sure the total resistance across the bond is no more than 0.001 ohm.
Q. Using a spring scale, determine hinge friction forces required to rotate the aileron a minimum of
0.67 inches up and down through neutral (zero) position. Aileron travel is measured using index plates shown on Fig. 403. All forces are to be measured at a point 12 inches aft of hinge centerline on each aileron.
NOTE: The aileron pressure must be applied very slowly and smoothly to prevent erroneous readings resulting from inertia.
R. Record forces required to move each aileron through neutral position as positive, and forces required to restrain aileron from moving through neutral position as negative.
S. Add forces with similar signs and subtract forces with different signs. Results must not exceed 5 pounds.
NOTE: If specified result exceeds 5 pounds, the aileron is binding at the hinge attachment points. Ensure all hinge bolts are adequately lubricated and check that hinge bolt torque values are as specified.
T. Using spring scale, measure force required to move each aileron from neutral position through full travel in each direction, then back to neutral. Apply force perpendicular to aileron chord plane at a point 12 inches aft of aileron hinge centerline. Travel shall be smooth and without binding. Maximum force required shall not exceed 3 pounds up and 13 pounds down.
NOTE: Full travel is not necessarily to the structural stops but rather to the distances shown in Fig. 403.
U. Deleted.
V. Connect aileron control rod to aileron (Fig. 404). Coat control rod bolt with primer and install with head outboard. Secure bolt with washer and nut. Tighten nut within 60 to 85 pound-inch torque range and install cotter pin.
W. Install rigging pin A/S-4 in aileron bus drum (Fig. 405).
X. Check that point B on aileron index plate aligns with point A on wing structure index plate within
0.03 inch, if not adjust ABSA and ABSB cables as follows:
(1) Remove turnbuckle locking clips.
500
Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-11 Page 405
T52448 G03498 G03505
Aileron Deflection Diagram 523
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