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NOTE: The airplane may pitch up or down during transition.
SUBTASK 27-11-00-280-004
(11) Make sure no large rolling movement and/or large pitch change occurs.
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EFFECTIVITY
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SUBTASK 27-11-00-750-002
(12) Do these steps to find and correct asymmetrical flight control forces:
(a) Trim the airplane with the rudder to keep wings level flight.
(b) Make sure that the rudder trim does not change by more than 2 units.
1) If the change is more than 2 units, do this task: Control Rod for Standby Rudder Power
Control Unit Adjustment, TASK 27-21-00-820-810-001 or Control Rod for Standby
Rudder Power Control Unit Adjustment, TASK 27-21-00-820-810-002.
2) If the standby rudder is in adjustment, do this task: Aileron Balance Tab Adjustment,
TASK 27-11-00-820-803.
(c) Make a note if there is a roll tendency.
(d) Turn the control wheel clockwise 30 degrees.
(e) Turn the control wheel counterclockwise 30 degrees.
(f) Make sure the control wheel forces are symmetrical.
1) If the control wheel forces are not symmetrical, measure the forces.
a) Use a force gauge, COM-1557 to push down on the right handgrip knob of the
control wheel, until the wheel is turned 30 degrees clockwise.
b) Measure the control wheel force.
c) Use a force gauge, COM-1557 to push down on the left handgrip knob of the control
wheel, until the wheel is turned 30 degrees counterclockwise.
d) Measure the control wheel force.
e) If the control wheel force in one direction is 2 or more times the force in the other
direction, do this task: Aileron Balance Tab Adjustment to Equalize Lateral
Manual Reversion Forces, TASK 27-09-71-820-802.
f) If the control wheel force in one direction is less than 2 times the force in the other
direction, no action is necessary.
SUBTASK 27-11-00-860-085
(13) Set the FLT CONTROL B switch in OFF.
SUBTASK 27-11-00-860-086
(14) Set the FLT CONTROL A switch to STBY RUD.
SUBTASK 27-11-00-750-003
(15) Do all the steps to find and correct asymmetrical flight control forces again.
SUBTASK 27-11-00-860-087
(16) Set the SPOILER A and B, FLT CONTROL A and B switches back to ON.
------------------------- END OF TASK ---------------------------
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EFFECTIVITY
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AILERON AND AILERON TRIM CONTROL SYSTEM - INSPECTION/CHECK
1. General
A. This procedure has these inspection tasks:
(1) Aileron Mechanical Components from the Control Wheel to the Aileron PCU’s.
(2) Aileron Mechanical Components from the Aileron PCU to the Aileron and the Flight Spoiler
Mechanical Control Path.
TASK 27-11-00-210-801
2. Aileron Mechanical Components Inspection - Forward components
(Figure 601)
A. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
B. Access Panels
Number Name/Location
112A Forward Access Door
C. Procedure
SUBTASK 27-11-00-010-005
(1) To get access to the aileron mechanical components, do this step:
Open this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-11-00-210-003
(2) Do a general visual inspection of the forward aileron mechanical components to include the
following:
(a) control wheels,
(b) aileron control drum,
(c) bus drums.
------------------------- END OF TASK ---------------------------
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Aileron and Aileron Trim Control System
Figure 601/27-11-00-990-810
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EFFECTIVITY
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TASK 27-11-00-210-802
3. Aileron Mechanical Components Inspection - from the Aileron PCUs to the Aileron and the Flight Spoiler
Mechanical Control Path
(Figure 601)
A. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
572 Left Wing - Aileron
672 Right Wing - Aileron
　
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