FLIGHT MANUAL TSA-M, VARIANT S6
Doc.-No.:P400-006.000 E
Page: 2-5
Revision: 9
Date of Issue: 07. October 2008
Agency approved
Date of Rev.: 01.10.2012
2.4 Limitations for Propulsion System
and Operating Fluids ____________________________
2.4.1
Engine Limitations
Engine
a) Engine Manufacturer
BRP-Rotax GmbH & Co. KG
Gunskirchen, Austria
b) Engine Model
ROTAX 914 F2
c) Maximum RPM during T/O (max.
for 5 minutes):
5600 RPM
(5800 RPM allowed for max. 1 min)
d) Maximum Continuous RPM
5500 RPM
e) Idle RPM:
1200 to 1400 RPM
f) Max. T/O-Power (ISA):
113.3 HP / 84.5 kW at 5800 RPM
(Takeoff RPM limited to 5600 RPM by
const. speed propeller control)
g) Max. Continuous Power:
98.4 HP / 73.4 kW at 5500 RPM
h) Max. Altitude with Constant
Power:
•
T/O-Power
•
Continuous Power
To max. 8000 ft / 2450 m MSL
To max. 16000 ft / 4875 m MSL
Max. Cylinder-Head Temperature
(CHT):
minimum
maximum
122°F / 50°C
275°F / 135°C
i) Fuel Pressure:
minimum
normal
maximum
Air-Box Pressure
+ 4.43 inHg / 1.5 x 10
-1
bar
+ 7.38 inHg / 2.5 x 10
-1
bar
+ 10.34 inHg / 3.5 x 10
-1
bar
j) Manifold-Air-Pressure:
max. T/O-Power
max. Continuous Power
40.5 inHg / 1.37 bar (acc. to ROTAX)
36.0 inHg / 1.22 bar (acc. to ROTAX)
Propeller
a) Propeller Manufacturer:
MT-Propeller Gerd Muehlbauer GmbH
D-94348 Atting, Germany
b) Propeller Model:
MTV-7-A/170-51
c) Control Unit:
P120-A
d) Type Certificate:
LBA TC: 32.130/84 R.3
