SECTION 7
DESCRIPTION
SOCATA
MODEL TB 20
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© 1988, 1991, 1992, 1994 to 1996, 1997, 2000 -
socata
- All rights reserved
June 30, 1988
Revision 6
7.9
A pointer indicator located on the right of the trim control wheel gives the
anti–tab position. Forward rotation of the control wheel will trim nose–down,
conversely, rearward rotation will trim nose–up.
Stabilator tab deflection with stabilator in maximum nose–up attitude must
be :
– nose–up
0
°
±
0.5
°
– nose–down
15
°
±
1.5
°
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.
Rudder tab deflection must be :
– to the right
10
°
±
2
°
– to the left
25
°
±
2
°
INSTRUMENT PANEL
L.H. instrument panel (see Figure
) is designed around the basic ”T”
configuration.
The gyros (if installed) are located in front of the pilot and arranged vertically.
The airspeed indicator or the true airspeed indicator and the altimeter are to
the left and right of the gyros, respectively.
The upper edge of the instrument panel contains the advisory panel
(see Figures
The left side of the panel contains lighting controls, emergency beacon
switch (if installed) and registration (enabling airplane radio call).
