Flight Controls

Question 1

The ( ) is moved left or right by a set of redundant cables that split in the burst area.

Answer 1

Rudder. PTM Pg. 15-9

Question 2

The auto-pilot, yaw dampener, and rudder boost system move the rudder via an ( ) yaw servo that clutches to and moves the rudder cables.

Answer 2

Auto-pilot yaw servo. PTM Pg. 15-10

Question 3

Depressing the ( ) switch on the pilot or co-pilot control yoke stops all trim motors and pitch trim bias.

Answer 3

Red MSW switch. PTM Pg. 15-2

Question 4

The ( ) are moved by a set of redundant cables that split in the burst zone. PTM Pg. 15-4

Answer 4

Elevators. PTM Pg. 15-4

Question 5

The ( ) moves the elevator via an auto pilot pitch servo that clutches to the elevator cables.

Answer 5

Auto-pilot. PTM Pg. 15-4

Question 6

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.

Answer 6

Elevator Disconnect Handle. PTM Pg. 15-4

Question 7

( ) are moved via a combination of control cables connected to the pilot and co-pilot control yokes.

Answer 7

Ailerons. PTM Pg. 15-5

Question 8

When the pilot control yoke is displaced more then ( ) degrees, wing spoilerons actuate assisting in increasing the aircraft’s roll rate.

Answer 8

5 Degrees. PTM Pg. 15-8

Question 9

Pulling the ( ) Disconnect handle disengages the pilot control yoke from the aileron cables.

Answer 9

Aileron Disconnect handle. PTM Pg. 15-8

Question 10

With ailerons disconnected, ( )control is through the pilot yoke only using spoilerons.

Answer 10

Roll Control. PTM Pg. 15-8

Question 11

The auto-pilot moves the ailerons via an auto pilot ( ) servo that clutches to the aileron cables.

Answer 11

Aileron servo. PTM Pg. 15-7

Question 12

To trim the rudder, a ( ) trim switch electrically moves a rudder trim tab.

Answer 12

Rudder trim switch. PTM Pg. 15-10

Question 13

To trim the aileron, an ( ) trim switch on either control yoke electrically moves an aileron trim tab on the left aileron.

Answer 13

Aileron trim switch. PTM Pg. 15-8

Question 14

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.

Answer 14

Elevator trim switch. PTM Pg. 15-12

Question 15

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.

Answer 15

Secondary Pitch Trim motor. PTM Pg.15-17

Question 16

Secondary Pitch Trim can be used by selecting ( ) on the Pitch Trim Switch.

Answer 16

SEC. PTM Pg. 15-15

Question 17

In the event of an un-commanded motion in the pitch, roll or yaw axis, the pilot should depress and hold the ( ) (MSW).

Answer 17

Control Wheel Master Switch. AFM Pg.s 3-27 and 3-31

Question 18

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.

Answer 18

Experiencing an un-commanded motion in the pitch, roll or yaw axis. QRH Pg. E-2

Question 19

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.

Answer 19

Flight control. QRH Pg. E-2

Question 20

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).

Answer 20

Stick shaker or stall. QRH Pg. E-38

Question 21

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 ( ).

Answer 21

Pitch Trim Bias. PTM Pg. 15-18

Question 22

When the auto-pilot trims the aircraft in pitch for more than 2 to 3 seconds, an ( ) clacker sounds.

Answer 22

Audible clacker. PTM Pg. 15-7

Question 23

The ( ) Bias switch is located next to the Rudder Boost switch, between the Clearance Delivery Radio and the Rotary System Test knob.

Answer 23

Pitch Trim. PTM Pg. 15-18

Question 24

When the spoilers are activated on the ground, they will always go to their full extension of ( ) degrees.

Answer 24

60 Degrees. PTM Pg. 15-28

Question 25

If the ( ) are disconnected, spoilerons can still continue to function as spoilers.

Answer 25

Ailerons. PTM Pg. 15-29

Question 26

In the event of an ( ) with the spoilers fully extended, roll augmentation is still available with the spoilerons.

Answer 26

Emergency descent. PTM Pg. 15-29

Question 27

Maximum speed for ( º) degrees of flaps is 250 KIAS.

Answer 27

8 Degrees. PTM Pg. 15-25

Question 28

Maximum speed for ( º) degrees of flaps is 200 KIAS.

Answer 28

20 Degrees. PTM Pg. 15-25

Question 29

Maximum speed for ( º) degrees of flaps is 150 KIAS.

Answer 29

40 Degrees. PTM Pg. 15-25

Question 30

The ( ) shaker activates just prior to the wing stalling.

Answer 30

Stall shaker. PTM Pg. 15-31

Question 31

A satisfactory test of the flaps using the Rotary System Test knob is indicated by the ( ) CAS messages FLAPS FAIL and FLAPS FAULT.

Answer 31

Amber CAS. PTM Pg. 15-25

Question 32

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.

Answer 32

Rudder Boost. PTM Pg. 15-12

Question 33

Rudder Boost must be “ ” for take off.

Answer 33

ON. PTM Pg. 15-12

Question 34

Do not extend flaps above ( ’ feet).

Answer 34

18,000. AFM Pg. 1-10

Question 35

Limit Maneuvering Load Factors:

Answer 35

• Flaps Up +2.9g’s to -1.0g’s

* Flaps Down +2.0g’s to -0.0g’s