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14) Install the rudder - refer to 55-40-00.
15) Perform a test flight - refer to 05-30-00.
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Validity : S / N 1 - 9999
Page 402
55-30-00
(CA) SEP 04
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Vertical stabilizer - Removal / Installation
Figure 401
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55-30-00 Page 403
(CA) SEP 04
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Validity : S / N 1 - 9999 55 30-00Page 404
(CA) SEP 04
RUDDER
DESCRIPTION AND OPERATION
1. GENERAL
The rudder has an entirely metal structure.
It enables the aircraft to be controlled around the yaw axis.
It is provided with a rudder tab allowing the pilot to apply less force on the rudder pedals in case of crosswind.
2. LOCATION (Figure 1)
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Rudder 1 320 / 55-40-00
Rudder tab 1 320 / 55-40-00
I 3. DESCRIPTION (Figure 2)
A. Rudder
The rudder is located aft the vertical stabilizer. It is articulated on two fittings which are secured to the spar of the vertical stabilizer.
The pilot controls the rudder via the rudder pedals and a rudder control linkage composed of rods, bellcranks and a lever secured to the rudder hinge pin.
I It is fitted with a balancing weight of 2.2 lbs (+0 ; +0.11) [1 kg (+0 ; +0.050)].
The top of the rudder is equipped with a composite material tip covering the balancing weight.
II A static discharger is secured to the tip trailing edge.
With the rudder pedals pushed fully forward, the rudder travel is 25° ± 2° to the left or to the right.
B. Rudder tab
I The rudder tab is located on the rudder lower trailing edge. It is articulated on the rudder by hinges.
The rudder trimming is accomplished by rotating a control knob (rudder trim) deflecting horizontally, located on the control pedestal. This trim actuates the rudder tab through a sheathed control. Rotating the trim to the right will trim nose-right ; conversely, rotating it to the left will trim nose-left.
The rudder tab travel must be :
- to the right 10° ± 2°,
- to the left 25° ± 2°.
ABAA
Validity : S / N 1 - 9999 55-40 00 (CA) SPEaPg e041
®
Rudder - Identification and location of components
Figure 1
ABAA
Validity : S / N 1 - 9999 55 40-00Page 2
(CA) JUN 01
Rudder - Balancing weight
Figure 2
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Validity : S / N 1 - 9999 55 40 00Page 3
(CA) JUN 01
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ABAA
Validity : S / N 1 - 9999 55 40 00Page 4
(CA) JUN 01
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