T52458
Aileron Deflection Diagram 523
27-11-71 Figure 501 Aug 01/95
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b) Loosen two locknuts on valve rod for lower aileron power unit and rotate adjusting sleeve so that rigging pin A/S-4 will fit.
CAUTION: DO NOT INSERT RIGGING PIN A/S-4 WHEN ADJUSTING VALVE ROD, AS DAMAGE TO COMPONENTS MAY OCCUR.
(9)
Provide systems A and B hydraulic power (Ref 27-11-0).
(10)
Position flight controls system A switch to OFF, and flight controls system B switch to ON.
(11)
Check that rigging pin A/S-4 fits freely in upper bus drum, if not:
(a)
Remove rigging pin A/S-4.
(b)
Loosen two locknuts on valve rod for upper aileron power unit and rotate adjusting sleeve so that rigging pin A/S-4 will fit without binding.
CAUTION: DO NOT INSERT RIGGING PIN A/S-4 WHEN ADJUSTING VALVE ROD, AS DAMAGE TO COMPONENTS MAY OCCUR.
(12)
Position flight controls system A and B switches to ON.
(13)
Check that rigging pin A/S-4 fits freely through both bus drums, and check that gaps between upper bus drum lug and stopbolts on lower bus drum are within limits (Fig. 502, Section AA).
(14)
If required, adjustment of valve rods and stopbolts should be accomplished to meet conditions in step (13).
(15)
Remove rigging pin A/S-4.
(16)
Rotate aileron control wheel hard over in both direction from neutral and check that ailerons deflect within limits specified in Fig. 501.
(17)
Tighten valve rod locknuts.
(18)
Tighten stopbolt locknuts and install lockwire.
(19)
Check autopilot system for proper roll inputs (Airplanes with rate gyro test switch on autopilot roll computer).
(a) Check that all autopilot circuit breakers on P6 panel are closed.
500
Jun 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-71 Page 503
G10968 W01793
Aileron Power Control Unit Installation 500
27-11-71 Page 504 Figure 502 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/77
501 Aileron Power Control Unit Adjustment
May 01/03 Figure 502 (Sheet 2) 27-11-71
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
Place A/P ENGAGE A switch to CMD and push HDG SEL button.
(c)
Set BANK LIMIT to 10 and HEADING knob to provide an indication of 10 degrees to the right of airplane heading.
(d)
Check that control wheel rotates clockwise.
(e)
Repeat set (c) to the left.
(f)
Check that control wheel rotates counterclockwise.
(g)
Disengage autopilot.
(20)
Remove systems A and B hydraulic power (Ref. 27-11-0, Maintenance Practices).
(21)
Remove electrical power if no longer required.
580
27-11-71 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/81
AILERON CENTERING SPRING AND TRIM MECHANISM - REMOVAL/INSTALLATION
1. General
A. The removal of the centering spring and trim mechanism is accomplished as an assembly. The disassembly instructions are covered in the applicable overhaul manual.
2. Equipment and Materials
A. Rigging Pins F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
A/S-4 A/S-13 -11 -8 0.309 - 0.311 0.309 - 0.311 6.7 + 0.25 3.7 + 0.25 AILERON BUS DRUM AILERON TRIM GEARBOX
B. Grease - MIL-G-23827, or Corrosion Preventive Compound, MIL-C-11796 (Ref 20-30-21)
C. Control Wheel Straightedge - SE27-0001
3. Remove Aileron Centering Spring and Trim Mechanism
A. Depressurize hydraulic systems A and B (Ref 27-11-0 MP).
B. Set aileron control wheels in neutral position by clamping a straightedge across upper ends of both control wheels. Set aileron trim control knob with pointer in zero trim position.
C. Insert rigging pin A/S-13 in aileron trim gearbox (Fig. 401).
D. Insert rigging pin A/S-4 through aileron bus drums.
E. Disconnect upper and lower reaction links from reaction support assemblies by removing cotter pins, nuts, washers, and bolts.
F. Disconnect upper and lower input rods from lever assemblies by removing nuts, washers, and bolts.
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