Tecnam P2006T - 4. Engine

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Section 1 – General
GENERAL FEATURES
4
th
Edition, Rev 0
3. CONTROL SURFACES TRAVEL LIMITS
Ailerons
Up 20° Down 17 ° ( 2°)
Stabilator (refer to Trailing Edge)
Up 4° Down 15° ( 2°)
Stabilator trim tab (refer to Trailing Edge)
Up 2°; Down 19° ( 2°)
Rudder
RH 26° LH 26° ( 2°)
Rudder trim tab
RH 20° LH 20° ( 2°)
Flaps
0°; 40° (- 2°)
4. ENGINE
Manufacturer
Bombardier-Rotax GmbH
Model
912 S3
Certification basis
FAR 33 - Amendment 15
Type Certificate
EASA TCDS no. E.121 dated 1 April
2008
Engine type
4 cylinders horizontally opposed with
1352 c.c. of overall displacement, liquid
cooled cylinder heads, ram-air cooled
cylinders, two carburetors, integrated re-
duction gear box with torsional shock ab-
sorber and overload clutch.
Maximum power (at declared rpm)
73.5 kW (98.6hp) @ 5800 rpm –5
minutes maximum.
69.0 kW (92.5hp) @ 5500 rpm (continu-
ous)
5. PROPELLER
Manufacturer
MT Propeller
Type Certificate
LBA 32.130/086 (MTV-21 series)
Model
MTV-21-A-C-F/CF178-05
Blades/hub
2 wood/composite blades – aluminum
hub
Diameter
1780 mm (no reduction allowed)
Type
Variable pitch - hydraulically controlled