Flight Controls Flashcards
The ( ) is moved left or right by a set of redundant cables that split in the burst area.
Rudder. PTM Pg. 15-9
The auto-pilot, yaw dampener, and rudder boost system move the rudder via an ( ) yaw servo that clutches to and moves the rudder cables.
Auto-pilot yaw servo. PTM Pg. 15-10
Depressing the ( ) switch on the pilot or co-pilot control yoke stops all trim motors and pitch trim bias.
Red MSW switch. PTM Pg. 15-2
The ( ) are moved by a set of redundant cables that split in the burst zone. PTM Pg. 15-4
Elevators. PTM Pg. 15-4
The ( ) moves the elevator via an auto pilot pitch servo that clutches to the elevator cables.
Auto-pilot. PTM Pg. 15-4
Pulling the ( ) Disconnect Handle electrically disengages the right elevator from the left elevator and mechanically de-clutches the left yoke from the right yoke in pitch.
Elevator Disconnect Handle. PTM Pg. 15-4
( ) are moved via a combination of control cables connected to the pilot and co-pilot control yokes.
Ailerons. PTM Pg. 15-5
When the pilot control yoke is displaced more then ( ) degrees, wing spoilerons actuate assisting in increasing the aircraft’s roll rate.
5 Degrees. PTM Pg. 15-8
Pulling the ( ) Disconnect handle disengages the pilot control yoke from the aileron cables.
Aileron Disconnect handle. PTM Pg. 15-8
With ailerons disconnected, ( )control is through the pilot yoke only using spoilerons.
Roll Control. PTM Pg. 15-8
The auto-pilot moves the ailerons via an auto pilot ( ) servo that clutches to the aileron cables.
Aileron servo. PTM Pg. 15-7
To trim the rudder, a ( ) trim switch electrically moves a rudder trim tab.
Rudder trim switch. PTM Pg. 15-10
To trim the aileron, an ( ) trim switch on either control yoke electrically moves an aileron trim tab on the left aileron.
Aileron trim switch. PTM Pg. 15-8
To trim the elevator, an ( ) on either control yoke electrically activates the Primary Pitch Trim motor, which moves the leading edge of the horizontal stabilizer.
Elevator trim switch. PTM Pg. 15-12
The auto-pilot trims the aircraft in pitch only, using the ( ) Pitch Trim motor, which in turn moves the leading edge of the horizontal stabilizer.
Secondary Pitch Trim motor. PTM Pg.15-17
Secondary Pitch Trim can be used by selecting ( ) on the Pitch Trim Switch.
SEC. PTM Pg. 15-15
In the event of an un-commanded motion in the pitch, roll or yaw axis, the pilot should depress and hold the ( ) (MSW).
Control Wheel Master Switch. AFM Pg.s 3-27 and 3-31
Experiencing an ( ) motion in the pitch, roll or yaw axis, the pilot can find the appropriate checklist using the table of contents in the red section of the QRH.
Experiencing an un-commanded motion in the pitch, roll or yaw axis. QRH Pg. E-2
In the event of a ( ) control jam, the pilot can find the appropriate checklist using the table of contents in the red section of the QRH.
Flight control. QRH Pg. E-2
In the event of a ( ), the pilot should immediately reduce the angle of attack and ensure the thrust levers are in TO or APR (if required).
Stick shaker or stall. QRH Pg. E-38
If the stabilizer jams, or in the event of a failure of both Primary and Secondary Pitch Trim motors, elevator control forces can be relieved when slowing down to configure by using ( ).
Pitch Trim Bias. PTM Pg. 15-18
When the auto-pilot trims the aircraft in pitch for more than 2 to 3 seconds, an ( ) clacker sounds.
Audible clacker. PTM Pg. 15-7
The ( ) Bias switch is located next to the Rudder Boost switch, between the Clearance Delivery Radio and the Rotary System Test knob.
Pitch Trim. PTM Pg. 15-18
When the spoilers are activated on the ground, they will always go to their full extension of ( ) degrees.
60 Degrees. PTM Pg. 15-28
If the ( ) are disconnected, spoilerons can still continue to function as spoilers.
Ailerons. PTM Pg. 15-29
In the event of an ( ) with the spoilers fully extended, roll augmentation is still available with the spoilerons.
Emergency descent. PTM Pg. 15-29
Maximum speed for ( º) degrees of flaps is 250 KIAS.
8 Degrees. PTM Pg. 15-25
Maximum speed for ( º) degrees of flaps is 200 KIAS.
20 Degrees. PTM Pg. 15-25
Maximum speed for ( º) degrees of flaps is 150 KIAS.
40 Degrees. PTM Pg. 15-25
The ( ) shaker activates just prior to the wing stalling.
Stall shaker. PTM Pg. 15-31
A satisfactory test of the flaps using the Rotary System Test knob is indicated by the ( ) CAS messages FLAPS FAIL and FLAPS FAULT.
Amber CAS. PTM Pg. 15-25
In order for ( ) Boost to aid in flight, the flaps must be extended beyond 3º degrees, the airspeed less than 180 KIAS, and their must be a significant rudder pedal force input.
Rudder Boost. PTM Pg. 15-12
Rudder Boost must be “ ” for take off.
ON. PTM Pg. 15-12
Do not extend flaps above ( ’ feet).
18,000. AFM Pg. 1-10
Limit Maneuvering Load Factors:
- Flaps Up +2.9g’s to -1.0g’s
* Flaps Down +2.0g’s to -0.0g’s
