5 - 4 Page Date: 6. April 2010
Pilot´s Operating Handbook
EXTRA 300LT
Section 5
Performance
TAKE-OFF
§ 5.5 shows the Take-Off Distance.
Example:
T/O Weight: 950 kg (2095 lbs)
Ground Roll: 223 m (732 ft)
(decreased by 8% due to headwind): 205 m (673 ft)
Total Distance to clear a 50 ft obstacle: 385 m (1263 ft)
(decreased by 8% due to headwind): 354 m (1161 ft)
These distances are well within the available field length in this sample problem.
CLIMB
§ 5.6 shows the Rate Of Climb Performance.
(conditions outlined in Fig. 5.6 deviate from the sample problem given here).
Pressure altitude: 5000 ft
Outside air temperatur: +5°C
Weight: 900 kg (1984 lbs)
Climb Rate: 2104 ft/min
§ 5.7 shows the Time, Fuel and Distance to Climb.
Example (climb from 2000 ft (610 m) to 8000 ft (2438 m)):
Time to Climb: (3.52 - 0,77) min = 2.75 min
Fuel to Climb: (7.63 - 1.67) Liters = 5.96 Liters
Distance to Climb: (5.71 - 1.19) nm = 4.52 nm
CRUISE
Cruise Altitude and Power Setting should be determined for most economical fuel
consumption and several other considerations.
§ 5.11 shows the Cruise Performance data for a T/O Weight of 950 kg (2095 lbs) with
maximum fuel (209 L).
The conditions in the examples of the following Figures are:
Pressure altitude: 8000 ft (2438 m)
Power Setting: 65 %
§ 5.8 shows the range: 562 nm (1041 km)
§ 5.9 shows the endurance: 3.3 h
§ 5.10 shows the cruise speed: 173 kts (320 km/h)
The desired total distance in this sample problem is well within this value.
DESCENT
§ 5.12 shows Descent Time, Distance and Fuel data.
Example (descent from 8000 ft (2438 m) to 2000 ft (610 m)):
Time to Descent : (8 - 2) min = 6 min
Distance to Descent : (21 - 5) NM = 16 nm
Fuel to Descent : (4 - 1) Liters = 3 Liters (0.79 US Gal.)
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