4) Monitor any roll tendency. Turn control wheel 30 degrees right and 30 degrees left. If wheel forces are symmetrical, or if not symmetrical only a small quantity, aileron tab rod adjustment is satisfactory. But if forces are not symmetrical at 2 to 1 or more, it is necessary to measure and record forces as follows: a) Use a push-pull scale to push down on control wheel handgrip knobs,
moving wheel 30 degrees right and 30 degrees left. Record values. b) After these measurements, set the spoiler A and B switches and flight control A and B switches back ON.
(f)
Repeat step (e), except with B in OFF and A in STBY RUD.
(g)
This completes flight test.
C. Tab Control Rod Adjustment
(1)
General
(a) If the values obtained above are asymmetrically greater than a 2 to 1 ratio, the aileron control tabs must be repositioned relative to the aileron. The control tabs are repositioned by changing lengths of the tab control rods (Fig. 510).
(2)
Adjust tab control rods.
NOTE: You can verify that the adjustments have been accomplished correctly by performing an additional flight test, although one is not necessary.
(a)
Depressurize hydraulic systems A and B (Ref 27-11-0 MP).
(b)
Adjust tab control rods. Refer to Aileron Tab Adjustment to equalize lateral manual reversion forces (Ref 27-09-400 A/T).
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AILERONS - REMOVAL/INSTALLATION
1. General
A. For interchangeability of graphite/composite ailerons with aluminum/fiberglass ailerons, refer to 27-09-800.
B. The aileron assembly consists of an aileron, balance tab, and balance panel. The balance tab is balanced by adding a specified number of adjust weights to balance panel. These weights are painted international orange and are installed on lower surface of balance panel hinge. The specific number of weights required for static balancing is marked on balance tab data plate (Fig. 401).
C. The replacement of a spare aileron may be accomplished using the old balance tab and balance panel. However, the number of adjust weights for balance tab must correspond with the data etched on tab data plate.
2. Equipment and Materials
A. Straightedge . 6 inches long
B. Spring Scale . graduated from 0 to 20 pounds
C. Grease . BMS 3-24 (Ref 20-30-21)
D. Sealant . BMS 5-95
E. Primer . BMS 10-11, Type I (Ref 20-30-41)
F. Enamel . BMS 10-11, Type II
G. Rigging Pins Kit . F7027-3, -52, -61, or -84:
H. Bonding Meter, Microhm Bridge, Type 2
Bonding Meter . 477W Antron Meter
Antron Manufacturing, Inc.
Cleveland, Ohio
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
A/S-4 -11 0.309 - 0.311 6.7 + 0.25 AILERON BUS DRUM
3. Remove Aileron
A. Remove four aileron access panels located on lower wing surface adjacent to leading edge of the aileron (Fig. 406).
B. Remove aft balance panel seal retaining bolts and retaining strip (Fig. 402).
C. Remove hinge pin retainer bolt, and extract hinge pins from aft balance panel hinge.
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D. Remove aileron hinge access panels (Fig. 406) at four hinge locations.
E. Lift aileron trailing edge up and remove control rod attach bolt (Fig. 404).
F. Disconnect balance tab pushrods (Fig. 401) from wing hinge fitting.
G. Disconnect bonding jumpers at number 1 and 4 hinge locations.
H. Support aileron.
I. Remove cotter pins and nuts from hinge bolts at four hinge locations and remove hinge bolts.
J. Remove aileron from wing.
NOTE: The aileron, balance tab and balance panel weigh approximately 75 pounds as an assembly. The aileron alone weighs approximately 63 pounds.
K. If old balance tab is to be used, remove balance tab from old aileron (Ref 27-11-21, R/I).
4. Install Aileron
A. Check wear on aileron (Ref Aileron - Inspection/Check).
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