Rigging Report
STEMME S12
Document-No.:
1001-08-S12-2
DE.21G.0068
Page 1 (of 2)
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Rutz
01.08.2011
1001-08-S12-2_Rigging_S12.doc-1/17.08.16 15:33/23.03.17 13:08
Serial Number:
12-
Registration:
-
Order No.:
Drawing Up Reason:
Conformity Inspection
Inspection. Date of Finding Report:
Other:
1. Angle of Incidence
The following rated values and actual values of the angles of incidence apply to the upper edge of a wedge 1000:84 on the
straight part of the tail cone, with its vertex in flight direction.
Inspection of the angle of incidence is required for the Conformity Inspection and an Inspection following a heavy landing,
furthermore after Major Repair, if wing and/or tail mountings have been affected.
Rated
Reading
Angle of Incidence of the Wing Chord:
+2.0° ± 0.2°
°
Angle of Incidence of the Horizontal Tail Chord:
-2.0° ± 0.2°
°
Secondary Condition: The difference of actual angles of incidence wing/horizontal tail must be
between 3.7° and 4.4°
°
2. Control Surface Deflections
Positive values (+) indicate full control surface deflections downward or left, negative Values (-) indicate deflections upward
or right.
Elevator:
Measuring point is trailing edge of inner rib of elevator (140 mm / [5.51 in.] from hinge line).
Rated
Reading *
Rated
Reading *
Full Deflection:
- 44 +2/-5 mm
[-1.73 +0.08/-0.2 in.]
mm
[in.]
+ 44 +5/-2 mm
[+1.73 +0.2/-0.08 in.]
mm
[in.]
Rudder:
Measuring point is lower rear corner of control surface (420 mm / [16.5 in.] from hinge line).
Rated
Reading *
Rated
Reading *
Full Deflection:
+220 ± 15 mm
[+8.7 ± 0.6 in.]
mm
-220 ± 15 mm
[-8.7 ± 0.6 in.]
mm
[in.]
[in.]
Wing Flaps and Ailerons:
Flap
Lever
Position
Control
Stick
Position
Measurement points:
1) 1) aileron: inner rib of the control surface, 163 mm / 6.42 in. from hinge line.
2) 2) wing flap: inner rib of the control surface, 175 mm / 6.89 in. from hinge line.
left aileron
left wing flap
right wing flap
right aileron
Rated
mm [in.]
Reading*
mm [in.]
Rated
mm [in.]
Reading*
mm [in.]
Rated
mm [in.]
Reading*
mm [in.]
Rated
mm [in.]
Reading*
mm [in.]
- 10°
neutral
-31 ± 4
[-1.22 ± 0.16]
-31 ± 4
[-1.22 ± 0.16]
- 5°
neutral
-15 ± 4
[-0.6 ± 0.16]
-15 ± 4
[-0.6 ± 0.16]
0
left
-48 ± 4
[-1.89 ± 0.16]
+27 ± 3
[+1.06 ± 0.12]
neutral
0 ± 2
[0 ± 0.08]
0 ± 2
[0 ± 0.08]
0 ± 2
[0 ± 0.08]
0 ± 2
[0 ± 0.08]
right
+27 ± 3
[1.06 ±0.12]
-48 ± 4
[-1.89 ±0.16]
+ 5°
neutral
+15 ± 4
[+0.6 ± 0.16]
+15 ± 4
[+0.6 ± 0.16]
+ 10°
neutral
+31 ± 4
[+1.22 ± 0.16]
+31 ± 4
[+1.22 ± 0.16]
L (+16°) neutral
+51 ± 4
[+2 ± 0.16]
+51 ± 4
[+2 ± 0.16]
Содержание S12
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Страница 255: ...A FLIGHT CONTROLS PITCH CONTROL AND TRIM ...
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Страница 257: ...B FLIGHT CONTROLS LATERAL CONTROL WING FLAP AILERON ...
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Страница 259: ...C FLIGHT CONTROLS AIRBRAKE CONTROL ...
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Страница 261: ...D FLIGHT CONTROLS RUDDER CONTROL ...
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