CHAPTER 27 - FLIGHT CONTROLS 
TABLE OF CONTENTS / EFFECTIVITY 
CHAPTER/ SECTION  SUBJECT  GRID NO.  EFFECTIVITY 
27-20-00  RUDDER & TAB  2C6 
Rudder Control Cables Removal of Rudder Control Cables Installation of Rudder Control Cables Rigging and Adjustment of Rudder Controls  2C6 2C6 2C6 2C8 
Rudder Trim Controls 2C8 Removal of Forward Rudder Trim Controls 2C8 Installation of Forward Rudder Trim Controls 2C11 Removal of Aft Rudder Trim Controls 2C11 Installation of Aft Rudder Trim Controls 2C13 Rigging & Adjustment of Rudder Trim Controls 2C13 
Rudder Pedal Assembly Removal of Rudder Pedal Assembly Installation of Rudder Pedal Assembly  2C14 2C14 2C14 
27-30-00  STABILATOR & TAB  2C16 
Stabilator Control Cables Removal of Stabilator Control Cables Installation of Stabilator Control Cables Rigging and Adjustment of Stabilator Controls  2C16 2C16 2C18 2C21 
Stabilator Trim 2D2 Removal of Forward Stabilator Trim Assembly 2D2 Installation of Forward Stabilator Trim Controls 2D4 S-Tec Manual Electric Trim Clutch Check & Adjustment 2D5 Removal of Aft Stabilator Trim Controls 2D6 Installation of Aft Stabilator Trim Controls 2D6 Rigging and Adjustment of Stabilator Trim 2D6 
Stall Warning Horn and Lift Detector Removal of Lift Detector Installation of Lift Detector Adjustment of Lift Detector  2D8 2D8 2D8 2D9 
2B4  27-Cont./Effec. Page 27-4 Issued: April 1, 1997 

CHAPTER 27 - FLIGHT CONTROLS 
TABLE OF CONTENTS / EFFECTIVITY 
CHAPTER/ SECTION  SUBJECT  GRID NO.  EFFECTIVITY 

27-50-00  FLAPS  2D11 
Wing Flap Controls Removal of Wing Flap Controls Installation of Wing Flap Controls Rigging and Adjustment of Wing Flaps  2D11 2D11 2D12 2D13 

27-Cont./Effec. Page 27-5 Issued: April 1, 1997
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27-Cont./Effec. Page 27-6 Issued: April 1, 1997
GENERAL.
DESCRIPTION AND OPERATION.

The airplane is controlled in flight by the use of three axis control surfaces: consisting of ailerons (roll), stabilator (pitch), and rudder (yaw). Operation of these controls is through the movement of the control col-umn-tee bar assembly and rudder pedals. On the forward end of each control column is a sprocket assembly. A chain is wrapped around the sprockets to connect the right and left controls and then back to idler sprockets on the columns’ tee bar, which in turn connect to the aileron primary control cables.  The cables operate the aileron bellcrank and push-pull rods. The stabilator is controlled by a cable connected to the bottom of the tee bar assembly operating an aft fuselage bellcrank which controls a push rod connected to the balance arm of the stabilator.  Cables also connect the rudder pedals with the rudder sector.
Pitch and yaw trim control is provided by adjustable trim mechanisms for the stabilator and rudder, respec-tively.  The stabilator trim is controlled by a wheel and drum mounted on the floor tunnel between the front seats or, in an optional installation, by an S-Tec Manual Electric Trim Control mounted on the control yoke. Cables are routed aft from the drum to a screw assembly mounted above the stabilator attachment point. This screw assembly in turn moves the push rod which controls the stabilator trim tab. The rudder trim is controlled by a trim wheel behind the flap control lever.  Cables for the rudder trim are routed back through the fuselage and up into the tail where they attach to their aft actuator drum. The rudder tab is then driven by a push rod assembly connected to the actuator drum.
STANDARD PROCEDURES.
The following tips may be helpful where applicable in the individual control system procedures.
1.  
Turnbuckles must be assembled and adjusted in a manner that each terminal end is screwed an approximately equal distance into the barrel. During adjustment, the terminals must not be turned in a manner which would put a permanent twist in the cable.

2.  
After adjustment is completed, each turnbuckle must be checked. Not more than three terminal threads shall be visible outside the barrel. Locking clips must be installed and checked for proper installation by trying to remove the clips using fingers only.  Locking clips which have been installed and removed must be scrapped and new clips used.

3.  
Torque all nuts in the flight control surface rigging system in accordance with AC 43.13-1A or to torques specified within this manual text.

4.  
After completion of adjustment, each jam nut must be tightened securely and inspected.

5.  
On push rods or rod ends provided with an inspection hole, screws must be screwed in far enough to pass the hole. This can be determined visually or feel, by inserting a piece of wire into the inspection hole. If no inspection hole is provided, a minimum of 0.375 of an inch thread engagement must be maintained.
　
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