Section 7 - Airframe and Systems description - 2 - Airframe & Flight Controls

Question 1

Airframe

Question 2

Wing

Answer 2

Each wing consists of a central light alloy torque box which carries all the wing bending, shear and torque loads;

an aluminium leading edge is attached to the front spar while flap and aileron are hinged to the rear spar.

Question 3

torque box

Answer 3

houses an integrated fuel tank and supports the engine mount.

Question 4

Flap and aileron

Answer 4

respectively located inboard and outboard of wing and made up of light alloy, are constructed with a central spar to which front and rear ribs are jointed.

Question 5

What covers all the structures?

Answer 5

Wrappcd-around aluminium stressed skin panels

Question 6

How are the wings connected?

Answer 6

Steel alloy attachments connect left and right wing to each other.

Question 7

Fuselage

Answer 7

constituted by a light-alloy semi-monocoque structure wrapped around by stressed skin panels.

Question 8

What’s the material of radome and stern fairing?

Answer 8

composite material.

Question 9

What’s the cabing and baggage compartment floor made off?

Answer 9

warping of beans and keelsons supporting die seats guides and other components

Question 10

How’s the main landing gear sustained?

Answer 10

Two spar frames support on the top the wings attachments and on the bottom the sponson beans sustaining the main landing gear

Question 11

How’s the nose landing gear supported?

Answer 11

The forward frame, to which radome is connected, supports a steel trestle to which the nose landing gear is connected.

Question 12

How do the front and rear seat occur?

Answer 12

by means of two doors located in the opposite sides of the fuselage; a ditching emergency exit is available on the top of the cabin.H

Question 13

How’s the empennage supported?

Answer 13

In tail cone, two spar frames support the horizontal and vertical empennages attachments.

Question 14

Empannages

Answer 14

The vertical tail is entirely metallic:

vertical fin is made up of a twin spar with aluminium alloy stressed skin.

Rudder, providing directional control of the airplane, is made up of aluminium alloy.

Question 15

rudder

Answer 15

connected to the vertical tail at two hinge points.

A trim tab system increases directional stability of the airplane.

Question 16

horizontal empennage

Answer 16

all-moving type (stabilator); its structure consists of a twin spar to which front and rear ribs are jointed and it is covered by stressed aluminium alloy skin. ‘the trim tab completes the assy.

Question 17

Flight Controls

Answer 17

The main flight control system controls the airplane in three axes.

Question 18

Primary Controls

Answer 18

Ailerons, rudder and stabilator are manually operated by a conventional control column and rudder pedals, pulleys, cables, bellcranks and rods.

Question 19

secondary flight controls

Answer 19

consist of a two-axis trim system and a flaps system.

Question 20

Controls

Answer 20

Complete dual controls are provided for pilot and co-pilot.

Question 21

How does longitudinal control act?

Answer 21

through a system of push-pull rods connected to the control column and moving the stabilator whose anti-tab winglet works also as trim tab.

Autopilot pitch servo (if installed) is connected to the push-pull rods system through driving cables.

Question 22

How is longitudinal trim performed?

Answer 22

by a small tab positioned on the stabilator and manually operated via a control wheel positioned between the two crew seats

As optional, it is available an electrically operated longitudinal trim which it is also controlled by the autopilot system, when installed.

Question 23

How is trim position monitored?

Answer 23

by an indicator on the instrument panel. A trim disconnect toggle switch is provided.

Question 24

How is aileron controlled?

Answer 24

mixed type with push-rods and cables; a cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailerons differentially.

Question 25

How are the control wheels?

Answer 25

U-shaped, hinged on the top of the control column, control the ailerons.

Control wheel motion is transferred to the ailerons through a cable loop, up to the interconnecting rod linking the two push-pull rod systems which finally transmit the motion to the ailerons.

When either aileron control wheel is rotated, the crossover cable rotates the other control wheel.

Question 26

Aileron trim tab

Answer 26

The left aileron has a trim tab adjustable on ground: its deflection allows for lateral trimming of the airplane.

Question 27

How are both flaps extended?

Answer 27

via a single electric actuator controlled by a switch on the instrument panel.

Question 28

How do flaps act?

Answer 28

in continuous mode; the analogue indicator displays three markings related to 0°, takeoff (T/O) and landing (FULL) positions.

Question 29

How does the aural warning for the flaps work?

Answer 29

An aural warning is generated whenever the flaps are lowered to the FULL position and the landing gear is not down-locked.

Question 30

How is the rudder operated?

Answer 30

Rudder is operated through a cable system. A rudder trim tab allows aircraft directional trimming, especially in case of OEI operation: it is electrically operated via a switch located on the central console placed between crew seats.

Question 31

How is the rudder’s position monitored?

Answer 31

Its position is monitored by an indicator on the instrument panel. A trim disconnect toggle switch is provided.