POH
AQUILA AT01-200C
Section 7
AIRCRAFT DESCRIPTION
Document Nr.:
Issue:
Supersedes Issue:
Date:
Page:
FM-AT01-1010-106
A.01
--- (first issue)
02.03.2020
7 - 13
7.12 POWER PLANT
7.12.1 Engine
The ROTAX 914F is a 4 cylinder, 4 stroke horizontally opposed engine with liquid-
cooled cylinder heads and air-cooled cylinder barrels. It has brushless magnetos, 2
carburetors, 2 electrical fuel pumps, a reduction drive, an integrated alternator (
ALT2
),
an externally engine mounted alternator (
ALT1
) and an attachment for a hydraulic
constant speed propeller.
Additionally the engine contains an exhaust turbocharger. It is controlled by a Turbo
Control Unit (
TCU
), attached to the instrument panel, with sensors for temperature,
pressure and throttle valve position. The TCU controls a servo motor which, via a
bowden cable, adjusts a waste gate for manifold pressure and power control. An
additional intercooler for turbocharged air ensures, that air temperature behind the
turbocharger always remains within the operation limits of the engine.
Reduction ratio of internal gearbox:
2.43 : 1
Displacement:
73.9 in³
(1211 cm³)
max. takeoff power (5 min.):
113.3 BHP (84.5 kW)
at max. takeoff propeller speed:
2385 RPM
max. continuous power:
98.6 BHP (73.5 kW)
at max. continuous propeller speed:
2260 RPM
Further information can be found in the engine operating handbook.
7.12.2 Propeller
A two-blade, hydraulically controlled variable pitch propeller (constant speed propeller)
of wood-composite-hybrid construction.
Manufacturer:
mt-Propeller
Type:
MTV-21-A/175-05
Diameter:
68.9 in
(175 cm)
The propeller blades are wrapped in composite material and protected along the leading
edge by a stainless steel sheath. Near the blade root, the propeller is protected
additionally by a thick plastic film.