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.
(i)
Position flight controls system A switch to OFF, and flight controls system B switch to ON.
(j)
Check that rigging pin A/S-4 fits freely in upper bus drum, if not: 1) Remove rigging pin A/S-4. 2) Loosen two locknuts on valve rod for upper 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.
500
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523 Aileron Deflection Diagram
Oct 20/93 Figure 506 27-11-0
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(k)
Position flight controls system A and B switches to ON.
(l)
Check that rigging pin A/S-4 fits freely through both bus drums and gaps between upper bus drum lug and stop bolts on lower drum are within limits (Section A-A, Fig. 505).
(m)
If required, slight adjustment of valve rods and adjustments of stop bolts may be accomplished to meet conditions in step (l).
(n)
Remove systems A and B hydraulic power (Ref 27-11-0, Maintenance Practices).
(o)
Tighten valve rod locknuts and install lockwire.
(p)
Tighten stop bolt locknuts and install lockwire.
(q)
Remove rigging pins A/S-4 and A/S-13.
(r)
Remove straightedge from control wheels.
(6) Adjust aileron control bus cables ABSA and ABSB.
(a)
Install rigging pin A/S-4 (Fig. 504).
(b)
Check that left and right ailerons are in neutral position within 0.03 inch as shown in Fig. 506.
(c)
Check that cable tension on cables ABSA and ABSB on left and right wings is within values specified in Fig. 501.
(d)
If tension and/or aileron neutral position is not within limits, proceed as follows: 1) Adjust turnbuckles for each bus cable to permit positioning of ailerons to
specified neutral position.
2) Adjust cables to specified tension as shown in Fig. 501.
3) Install turnbuckle locking clips.
(e)
Check that aileron outboard trailing edge is below wing trailing edge 0.08 to 0.48 inch.
(f)
Remove rigging pin A/S-4.
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(7) Adjust aileron tab.
WARNING: HYDRAULIC SYSTEMS MUST NOT BE PRESSURIZED DURING THIS ADJUSTMENT, AS INJURY TO PERSONNEL MAY OCCUR.
NOTE: A flight test to determine and correct asymmetrical flight control forces must be performed following adjustment of the aileron tab control rods (Ref par. 3).
(a) With index mark on aileron aligned with index mark on wing within 0.03 inch, check mismatch between aileron trailing edge and aileron tab trailing edge. Using a straightedge or aileron tab alignment protractor, measure mismatch from trailing edge of tab to theoretical extension of aileron bottom surface, at three locations. Record measurement for later addition. 1) Take measurement 0.5 inch in from inboard end of tab. Check that tab trailing
edge aligns with an extension of aileron bottom surface within requirements shown on Fig. 510. Record measurement.
2) Take measurement 3.75 士0.25 inches in from outboard end of tab. Check that tab trailing edge aligns with an extension of aileron bottom surface within requirements shown on Fig. 510. Record measurement.
3) Take measurement at midpoint along tab. Check that tab trailing edge aligns with an extension of aileron bottom surface within requirements shown on Fig. 510. Record measurement.
(b)
Sum up dimensions taken and recorded in step (a). Sum must be between +0.12 and +0.30 inch.
(c)
Aileron balance tabs are repositioned relative to aileron by changing lengths of aileron tab control rods. These rods are shortened or lengthened in tab sets, a tab set being the two control rods which operate each individual tab. Shorten rods to lower tab trailing edge or lengthen rods to raise trailing edge as follows:
Adjustable Rod Tab Trailing Barrel Turns Edge Change
1 0.027 inch
2 0.054 inch
3 0.081 inch
4 0.108 inch
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