Flight Controls Flashcards
What do slats do
Lower stall speed by 35kts
How many multifunction spoiler per wing
4 , no 4 being outboard
Is there a flap slat reset
Yes through mcdu
How many flap slat resolvers per wing
4
How are flight controls configured
Mechanical flight controls on the Global series aircraft include manual operation of the ailerons, elevators and rudder, aileron and rudder trims, and their indicating systems. The ailerons and elevators use two hydraulic power control units (PCUs) on each flight control surface while the single rudder has three PCUs. The PCUs use different hydraulic systems as sources, allowing control of the aircraft in flight as long as any one hydraulic system is operating. Manual inputs from the cockpit move control cables and rods to the servovalves on the PCUs. Left and right aileron and elevator control circuits can separate and operate independently in the event of a jam. Electric trim inputs are fed into the control runs of the aileron and rudder system. Pitch trim will be covered under electronic flight controls.
How much force to disconnect ailerons
40lbs of force
In the unlikely event of a jam aft of the forward quadrant, increased pressure on the handwheel will actuate the disconnect mechanism. This will separate the left and right aileron circuits and allow the pilot with the free aileron to control aircraft roll. The disconnect mechanism latches when actuated and can only be reset manually at the disconnect mechanism itself by maintenance personnel.
Smart pcus
As the pressure decreases they lock in position
What is a compensator
A built-in compensator in each PCU traps the fluid in the PCU cylinders under pressure for flutter damping purposes should the hydraulic supply system fail. There is a visual indicator to verify the integrity of the compensator. There is a test port that will be used to check for an excessive internal leakage rate. There is also a jam check knob. This is used to check for the proper operation of the control valve internal jam protection feature.
Elevator gain changer mechanism, what does it do
Gain Change Mechanism Figure A18 The gain change mechanism provides the elevator system with a variable response rate. With the control column near the neutral position, the elevators are less responsive to inputs. As the control column moves farther from the neutral position, the elevators become more responsive to inputs. This provides a smoother flight when the pilot is hand flying the aircraft. There is a provision for a rigging pin in the gain change mechanism.
What is pitch disconnect mechanism
Similar to the aileron system, the pitch disconnect mechanism will operate automatically in the event of a cable jam in one circuit. When sufficient force is applied, approximately 50 pounds, the roller will ride up on the cam, allowing the use of the free circuit. Here, however, the disconnect mechanism does not lock out. The spring-loaded roller continues to ride up and down along the cam as inputs are provided to the elevator. Therefore, operation of the unjammed circuit requires the pilot to maintain the disconnect pressure on the column. There is a lock solenoid on this mechanism to inhibit the operation of the disconnect mechanism when the stick pusher activates during a impending stall. This will ensure the left and right elevator circuits will operate together during a stall recovery. A switch mounted on the mechanism provides a signal to the autopilot system to disengage the autopilot whenever a pitch disconnect occurs.
Force for elevator disconnect
When sufficient force is applied, approximately 50 pounds, the roller will ride up on the cam, allowing the use of the free circuit.
Elevator pitch feel unit
The pitch feel system is installed to provide the pilot with an artificial feedback, simulating the feel of the changing airload. The pitch feel system also provides automatic centering of the control column when input forces are removed. This is accomplished through the use of a pitch feel simulator unit that is mechanically connected to the left and right aft elevator quadrant. The control column forces vary with airspeed.
Does rudder have load limiter
Load Limiters Figure A32 Three adjustable load limiters are mounted on a common rotary torque tube that rotates in response to input from the rudder pedals. A balance spring supports the weight of the torque tube and load limiters in the case of an input disconnect. One load limiter provides the input to each rudder power control unit (PCU). Load limiters provide protection if one of the PCU main control valves should jam. The load limiter at the jammed position would compress or expand while the rotary torque tube continues to provide the operating PCUs with normal inputs.
How many pcu,s for rudder
3, syst 1,2,3
How many FCM,s
FCM 1a,1b,2a,2b
