1.
2.
3.
4.
5.
Wing-fold interlock mechanism
11. Flaperon actuator (left wing)
Filter
12. Crossover cables
Flaperon pop-up mechanism and cylinder
13. Pushrods
Left wing flaperons
14. Throttle quadrant
Flaperon control linkage
Figure 1-5.—Flaperon control system.
Wing fold flaperon interlock switch
6.
Flaperon control linkage
7.
Right wing flaperons
8.
Flaperon actuator (right wing)
9.
Flaperon pop-up valve
10.
Longitudinal Control Systems
Longitudinal control systems control pitch about the
lateral axis of the aircraft. Many aircraft use a con-
ventional elevator system for this purpose. However,
aircraft that operate in the higher speed ranges usually
have a movable horizontal stabilizer. Both types of
systems are discussed in the following text.
ELEVATOR CONTROL SYSTEM.—A typical
conventional elevator control system is operated by the
control stick in the cockpit, and is hydraulically powered
by the elevator power mechanism.
The operation of the elevator control system is
initiated when the control stick is moved fore or aft.
When the stick is moved, it actuates the control cables
that move the elevator control bell crank. The bell crank
transmits the movement to the power mechanism
through the control linkage. In turn, the power
mechanism actuates a push-pull tube, which deflects the
elevators up or down. If the hydraulic system fails, the
cylinder can be disconnected. In this condition the
controls work manually through the linkage of the
mechanism to actuate the elevators.
HORIZONTAL STABILIZER CONTROL
SYSTEM.—Horizontal stabilizer control systems are
given a variety of names by the various aircraft
manufacturers. Some aircraft systems are defined as a
unit horizontal tail (UHT) control systems, while others
are labeled the stabilator control system. Regardless of
the name, these systems function to control the aircraft
pitch about its lateral axis.
1-7
