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.

副翼位于每個(gè)機(jī)翼前緣外側(cè)，其它副翼組件位于 3個(gè)主要區(qū)域：
. 駕駛艙控制輪位于駕駛艙前部。副翼配平開關(guān)位于控制臺上。

. 輪艙區(qū)域副翼動力控制組件（ PCU，轉(zhuǎn)變駕駛員或自動駕駛系統(tǒng)機(jī)械驅(qū)動的輸

入為液壓驅(qū)動機(jī)械輸出，用以驅(qū)動副翼）位于主輪艙前壁。自動駕駛副翼作動筒主輪艙前壁。副翼位置傳感器從副翼系統(tǒng)提供兩個(gè)位置反饋信號給自動駕駛系統(tǒng)。
. 機(jī)頭下方控制鼓及轉(zhuǎn)動鼓輪連接到控制輪上，位于機(jī)頭下方。橫滾駕駛盤操縱反向換能器連接在轉(zhuǎn)動鼓輪與控制鼓之間，力量轉(zhuǎn)換器的輸出為自動駕駛提供信號。副翼操縱力限制器限制控制輪在自動駕駛儀操作時(shí)移動�？刂戚喌霓D(zhuǎn)動被限制在襟翼上升 17°及襟翼下降 25°之間。

(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.

升降舵操作要考慮飛機(jī)相對于升力中心的平衡。重力中心一般在升力中心的前面。安定面提供一個(gè)反向力給重力中心。安定面也可以在需要時(shí)通過配平改變力量以保持平衡。升降舵用來改變飛機(jī)俯仰姿態(tài)。移動升降舵離開它們的流線型位置，使得飛機(jī)改變水平軸上的俯仰姿態(tài)。升降舵的移動量形成俯仰率。當(dāng)達(dá)到希望的姿態(tài)時(shí)，升降舵再成流線型，飛機(jī)保持新的俯仰姿態(tài)。