(g)
Installation of a replacement aileron tab front spar hinge.
(h)
Installation of replacement bushings on the aileron tab front spar hinge nearest the tab control rods.
(i)
Installation of replacement tab control rods.
NOTE: For each aileron tab, if both control rods are adjusted (AMM 27-11-11/401), then flight test is necessary. If only one rod is adjusted and you can verify that the remaining rod has not been replaced or adjusted since the last flight test, then flight test is not necessary. If only one rod is adjusted and you can not verify that the remaining rod has not been replaced or adjusted since the last flight test, then flight test is necessary.
(j)
Installation of the original tab control rods if their adjusted lengths were changed.
NOTE: Installation of the original tab control rods does not make a flight test necessary if their adjusted length was not changed and they are installed in their original locations.
(k)
Installation of the original tab control rods if the aileron and/or tab were also removed from the airplane.
May 01/01 27-11-0
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B. Flight Test Procedure
(1)
Equipment and Materials
(a) Push-pull Scale 0-50 Pound Capacity (suitably padded to push down on control wheel handgrip knob)
(2)
Prepare for Test
(a) In order for the flight test to yield valid data, it is necessary that trim requirements be held to certain limits. Therefore, appropriate system or systems should be readjusted prior to flight test if any of following conditions are known to exist: 1) Aileron trim requirement more than 3/4 unit 2) Rudder trim requirement more than 1/2 unit
(3)
Test for Asymmetrical Flight Control Forces
(a)
The airplane should be tested under the following straight and level flight conditions: 1) Indicated Airspeed: 250 knots 2) Altitude: 5000 feet above ground level or higher 3) EPR and N1 equal for both engines 4) Wing fuel loads equal 5) Aileron trim requirement 3/4 unit or less 6) Rudder trim requirement 1/2 unit or less 7) Flaps up 8) All personnel seated
(b)
After the above flight conditions have occurred, center the control wheel and position spoiler switches A and B to OFF.
(c)
Position flight control switch B to ON and A to OFF in that order.
NOTE: Airplane may pitch up or pitch down during the transition.
1) Carefully move elevators, ailerons, and rudder. 2) Make sure that control forces and responses do not change.
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543 Aileron Tab Alignment
Feb 15/81 Figure 510 27-11-0
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(d) Position flight control switch A to ON and B to OFF in that order.
NOTE: Airplane may pitch up or pitch down during the transition.
1) Carefully move elevators, ailerons, and rudder.
2) Make sure that control forces and responses do not change.
(e) Position flight control switch B to STBY RUD and A to OFF in that order. Do the following.
NOTE: Airplane may pitch up or pitch down during the transition.
1) Check that the airplane pitch up or pitch down does not exceed 3 turns of the stabilizer trim wheel. If this value is exceeded, do the following: a) Verify that the Mach trim actuator has been correctly nulled; and that the
rigging of the elevator control pushrods, elevator power control unit input rod, the elevator feel and centering unit output rod are correct (Ref 27-31-0 A/T).
b) If the rigging checks are satisfactory, then verify that the elevator tab position measuring tool calibration is correct. You do this by verifying that a straight line across the two support pads on the tool projects to a point that is 0.22 inch below the reference point to which the elevator tab is to be aligned.
c) If the rigging tool calibration is correct then do the adjustment "Adjust the
elevator tab pushrods after the flight test" (Ref 27-31-0 A/T).
2) Trim the airplane using the rudder to keep heading with wing level.
3) Make sure that rudder trim does not change more than 1-1/2 units. If the trim
changes by more than 1-1/2 units, do as follows: a) Adjust the standby rudder system (Ref AMM 27-21-00/501, "Adjust the input rod of the standby rudder actuator"). b) If the standby rudder is in adjustment, do a check of the aileron tab adjustment (Ref AMM 27-11-00/501).
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