The control wheels are located in the forward portion of the flight deck. The aileron trim switch is located on the control stand.

.  Wheel well area

The aileron power control units(PCU, convert a pilot or autopilot mechanical driven input to a hydraulic power driven mechanical output to drive the aileron) are located on the forward wall of the main wheel well. The autopilot aileron actuators are located on the forward wall of the main wheel well. The aileron position sensor provides two feedback postion signal from the aileron system to the A/P system.

.  Lower nose compartment The control drum and bus drum are connected to the control wheel, located in the lower nose compartment. The roll CWS force transducer is connected between the bus drum and the control drum, the output of the force transducer provides signals to the autopilot. The aileron force limiter limits control wheel movement during A/P operation, the control wheel rotation is limited to 17°with flaps up and 25°with flaps down.

副翼位于每个机翼前缘外侧，其它副翼组件位于 3个主要区域：
. 驾驶舱控制轮位于驾驶舱前部。副翼配平开关位于控制台上。

. 轮舱区域副翼动力控制组件（ PCU，转变驾驶员或自动驾驶系统机械驱动的输

入为液压驱动机械输出，用以驱动副翼）位于主轮舱前壁。自动驾驶副翼作动筒主轮舱前壁。副翼位置传感器从副翼系统提供两个位置反馈信号给自动驾驶系统。
. 机头下方控制鼓及转动鼓轮连接到控制轮上，位于机头下方。横滚驾驶盘操纵反向换能器连接在转动鼓轮与控制鼓之间，力量转换器的输出为自动驾驶提供信号。副翼操纵力限制器限制控制轮在自动驾驶仪操作时移动。控制轮的转动被限制在襟翼上升 17°及襟翼下降 25°之间。

(4) To understand elevator poeration consider the airplane balanced about the center of lift (CL). The center of gravity (CG) is shown forward of the center of lift. The stabilizer provides a counter force to the CG. The stabilizer may be trimmed to changer the force as required to maintain balance. The elevators are used to change the pitch attitude. Moving the elevators out of their faired position causes the airplane to change the pitch attitude about the lateral axis. The amount of elevator movement establishes the airplane pitch rate. When the desired attitude is reached, the elevators are faired and the air-plane maintains the new pitch attitude.

升降舵操作要考虑飞机相对于升力中心的平衡。重力中心一般在升力中心的前面。安定面提供一个反向力给重力中心。安定面也可以在需要时通过配平改变力量以保持平衡。升降舵用来改变飞机俯仰姿态。移动升降舵离开它们的流线型位置，使得飞机改变水平轴上的俯仰姿态。升降舵的移动量形成俯仰率。当达到希望的姿态时，升降舵再成流线型，飞机保持新的俯仰姿态。