Copyright of RotorSport UK Ltd
Document number RSUK0060
Page 16 of 101 Page issue 5.1, dated 10.06.14
2.5 ENGINE
Manufacturer:
Bombardier Rotax, Gunskirchen/A
Type:
Rotax 912 ULS or Rotax 914UL
Take-off power:
100 HP/5800 rpm (for 5 minutes max operation), 115HP/5800
for the 914UL (for 5 minutes max operation)
Continuous duty:
90 HP/5500 rpm 912ULS, 100 HP/5500rpm 914UL
Cylinder head temperature: max. 135 °C
Oil temperature:
max. 130 °C
Propellers:
HTC 3 blade. Pitch angle: 20.5deg 912ULS, 22deg 914UL (ground
adjustable to suit engine and working environment). Take account of the propeller
concave face whilst measuring (see maint. Manual RSUK0061). Propeller is pitched for
max ground rpm of 5500.
IVO-prop DL3-68 in-flight variable pitch propeller – see section 9
For further data refer to the engine manual and parts catalogue.
WARNING! The engine must not be run without the propeller fitted – doing so may
result in severe engine damage.
2.6 ENGINE INSTRUMENTS
The following engine values are placarded on the instruments:
Note that, other than the engine rpm, the gauges are marked with these values internally.
Range
Maximum value
Unit
of
measurement
Engine RPM
Green 1600 - 5500
Amber 5500 - 5800/5min,
red line 5800.
rpm
Oil temperature
50 - 130
130 max
°C
Cylinder
head
temperature
to 135
135 max
°C
Oil pressure
0.8bar min to 3,500
rpm,
1.5bar
min
above 3,500rpm.
Normal range 2-5bar
7 (cold weather starting)
Bar
2.7 WEIGHT & BALANCE
The maximum take-off weight (MTOW) of the Calidus is 500kg. Marked on the aircraft,
and on the aircraft AWC, is the
actual
aircraft empty weight with unusable fuel. The
Payload is the MTOW minus the empty weight, and represents the allowance available for
occupants, fuel and luggage.
If any accessories are fitted which increase the empty weight of the aircraft then the
aircraft’s maximum payload must be reduced accordingly.
The pilot is responsible for ensuring the aircraft is not flown overweight.
NOTE! Flying the aircraft overweight invalidates your Permit to Fly.
The maximum permissible positions of the centre of gravity may not be exceeded.
The centre of gravity of the aircraft type was determined during Section T Compliance
evaluation. The envelope operational extremes were evaluated and shown to be
satisfactory. However operation outside of these evaluated points is not permitted!
