(3)
Adjust aileron control cables AA and AB.
(a)
Remove all rigging pins.
(b)
Place control wheels in neutral by clamping a straightedge across upper ends of both control wheels. One end of first officer's control wheel may be out of contact by a maximum of 0.20 inch.
(c)
Ensure that aileron trim knob indicator is in zero trim position and that trim roller is properly detented against cam.
(d)
Tension right and left AA and AB cables to values specified (Fig. 501).
NOTE: The aileron trim pointers (located on the top of both control wheels) must align with the zero indication on the aileron trim scales (located at the top of each control column) to 士0.02 inch. Replace pointer if needed.
(e)
Remove straightedge from control wheels.
(f)
Rotate aileron control wheel through several cycles.
(g)
Insert rigging pins A/S-1, A/S-1A, A/S-3 and A/S-13.
(h)
Check that tension in right and left AA and AB cables is within values specified (Fig. 501).
(i)
Install turnbuckle locking clips.
(j)
Remove all rigging pins.
(4)
Adjust aileron spring cartridge.
506
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-0 Page 511
WARNING: HYDRAULIC SYSTEMS MUST NOT BE PRESSURIZED DURING THIS
ADJUSTMENT AS INJURY TO PERSONNEL MAY OCCUR.
(a)
Install rigging pins A/S-3 and A/S-4 (Fig. 504).
(b)
Remove cotter pin, nut and washer from bolt which retains lock end of spring cartridge.
(c)
Check bolt which retains lock end of spring cartridge for freedom of movement without binding.
(d)
If bolt is found to be binding, adjust spring cartridge as follows: 1) Remove bolt and loosen locknut. 2) Rotate spring cartridge rod end as necessary to insert bolt without binding. 3) Tighten locknut to 10-20 pound-inches. 4) Ensure that antirotation fork and drain holes are down. 5) Install bolt and secure with washer, nut and cotter pin.
(e)
Remove rigging pins A/S-3 and A/S-4.
(5) Adjust aileron power control unit valve rods.
(a)
Position aileron control wheels in neutral position by placing a straightedge across the upper ends of the control wheels (Fig. 503). Position aileron trim control knob in zero trim position. Insert rigging pin A/S-13. Ensure that trim roller is properly seated against cam detent.
(b)
Ensure that hydraulic systems A and B are not pressurized.
(c)
Insert rigging pin A/S-4 (Fig. 504).
(d)
Check that valve lever on each power control unit is centered between stops (Detail B, Fig. 505).
CAUTION: DO NOT REMOVE VALVE LEVER WITH POWER CONTROL UNIT INSTALLED IN AIRPLANE, AS DAMAGE TO COMPONENTS MAY OCCUR.
506
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E41301 G03297G03298
500 Spring Cartridge Adjustment
Aug 01/94 Figure 504 27-11-0
Page 513
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Aileron Power Control Unit Adjustment 500
27-11-0 Figure 505 (Sheet 1) Aug 15/68
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500 Aileron Power Control Unit Adjustment
May 15/70 Figure 505 (Sheet 2) 27-11-0
Page 515
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(e) If valve levers are not centered between stops, proceed as follows:
WARNING: DO NOT REMOVE POWER CONTROL UNITS OR RELATED LINKAGES WITH HYDRAULIC POWER ON, AS INJURY TO PERSONNEL MAY OCCUR.
1) Loosen two locknuts on valve rod and rotate adjusting sleeve (Detail A, Fig. 505) to center valve lever between stops (Detail B, Fig. 505).
NOTE: Whenever a valve rod is being replaced, rod should be trial adjusted to meet dimensions specified in Detail A, Fig. 505.
2) Remove rigging pin A/S-4.
(f)
Provide systems A and B hydraulic power (Ref 27-11-0, Aileron and Aileron Control System - Maintenance Practices).
(g)
Position flight controls system A switch to ON and flight controls system B switch to OFF.
(h)
Check that rigging pin A/S-4 fits freely in lower bus drum, if not: 1) Remove rigging pin A/S-4. 2) Loosen two locknuts on valve rod for lower aileron power unit and rotate
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