(1)
Location Zone 101 Control Cabin, LH 102 Control Cabin, RH 306 Wing Trailing Edge, Aileron and Control Tab, LH 406 Wing Trailing Edge, Aileron and Control Tab, RH
(2)
Access Panel 7218 Access Panel, Wing Lower Surface, LH 8108 Aileron Access Panel, Wing Upper Surface, LH 7418 Access Panel, Wing Lower Surface, RH 8808 Aileron Access Panel, Wing Upper Surface, RH
D.
Install the Aileron Wing Quadrant
S 224-008
(1) Do this task: "Aileron Wing Quadrant Inspection/Check" (Ref 27-11-24/601).
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27-11-24
ALL ú ú 01 Page 404 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
POINT B
____ WITH THE AILERON SYSTEM ADJUSTED,
NOTE: POINT B ON EACH AILERON MUST ALIGN VERTICALLY WITH POINT A TO |0.03 INCH.
Aileron Deflection Diagram Figure 403
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27-11-24
ALL ú ú 01 Page 405 ú Jul 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
1 TEMPERATURE `F CABLE TENSION (POUNDS)
CABLES ABSA AND ABSB32
+10 -40 -30 -10 30 50 70 90 110 66 77 96 113 131 148 165 184 202
TO GET THE CORRECT CABLE TENSION, PERMIT A FOR THE NECESSARY REGULAR CHECKS WITHOUT
MINIMUM OF ONE HOUR AT A CONSTANT AMBIENT THE SYSTEM DISCREPANCY REPORTS, THE CABLE
TEMPERATURE OF |5`F FOR THE AIRFRAME TENSIONS CAN CHANGE +15/-30 POUNDS FROM THE
TEMPERATURE TO BECOME STABLE TABLE I VALUES. FOR THE CABLE TENSION CHECKS
THE CABLE LOADS MUST NOT BE MORE THAN ADJUST THE SYSTEM +10/0 POUNDS OFF THE TABLE I VALUES WHEN YOU THAT ARE THE RESULT OF THE SYSTEM DISCREPANCY REPORTS, THE TENSIONS CAN CHANGE |15 POUNDS FROM THE TABLE I VALUES. WHEN YOU ADJUST THE
CABLES, TABLE I VALUES MUST BE MET Aileron System Cable Tension Requirements
Figure 404
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ú 01 Page 406
ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 424-009
(2) Install the wing quadrant:
(a) If it is necessary, assemble the wing quadrant with the steps
that follow:
1) Install the bearings (swaged), bushing, and spacer with
bolt, washer, and self locking nut in the attach point of
the wing quadrant, if they are not installed (Fig. 401).
2) Tighten the self locking nut to 160-200 pound-inches.
(b) Put the aileron control rod in position to be connected to the
aileron hinge (structure) and to the wing quadrant clevis with
the steps that follow:
1) Install the bushing in the aileron control rod attach
point, if it is not installed.
2) Put the bushing in the aileron hinge (structure), if it is
necessary.
3) Put the wing quadrant in its position.
4) Install the bolt, washer, and nut at the aileron rod
end/aileron hinge joint.
5) Tighten the nut to 60-85 pound-inches.
6) Install the cotter pin.
(c) Put the cables ABSA (for the left wing) and ABSB (for the right
wing) in the bottom groove of the wing quadrant.
(d) Put the cables ABSB (for the left wing) and ABSA (for the right
wing) in the top groove of the wing quadrant.
(e) Install the cable retaining plates with screws, washers, and
nuts.
(f) Install the cable guard on the structure at the forward edge of
the wing quadrant.
(g) Adjust the cable guard clearance to 0.03 +0.05/-0.03 inch
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