曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

conditions are for a standard day (refer to Section 1). Flap position as
well as power setting technique is similarly noted with each table.
The charts in this section provide data for ambient temperatures from
–20 C (–4 F) to 40 C (104 F). If ambient temperature is below the
chart value, use the lowest temperature shown to compute
performance. This will result in more conservative performance
calculations. If ambient temperature is above the chart value, use
extreme caution as performance degrades rapidly at higher
temperatures.
All fuel flow data for cruise is based on the recommended lean mixture
setting detailed in Section 4 – Normal Procedures.
Serials 1337 and subsequent with SRV standard configuration:
Airplane performance is decreased without the nose landing gear
fairing installed. Refer to performance tables for specific values.
March 2010
5-4 Information Manual
Section 5 Cirrus Design
Performance Data SR20
Flight Planning
The performance tables in this section present sufficient information to
predict airplane performance with reasonable accuracy. However,
variations in fuel metering, mixture leaning technique, engine &
propeller condition, air turbulence, and other variables encountered
during a particular flight may account for variations of 10% or more in
range and endurance. Therefore, utilize all available information to
estimate the fuel required for a particular flight. Additionally, verify that
the weather, field length, wind, anticipated turbulence, and other
conditions that affect aircraft performance are judged to be satisfactory
and conducive to safe operations and compliant with the Federal
Aviation Regulations (FARs) or governing regulations, as applicable.
• Note •
Whenever possible, select the most conservative values from
the following charts to provide an extra margin of safety and to
account for events that could occur during a flight.
Sample Problem
The following sample flight problem uses information derived from the
airplane performance charts and tables to determine the predicted
performance for a typical flight.
The first step in flight planning is to determine the aircraft weight and
center of gravity, as well as information about the flight. For this
sample problem, the following information is known:
Airplane Configuration:
• Takeoff weight........................................................3000 Pounds
• Usable fuel.................................................................56 Gallons
Takeoff Conditions:
• Field pressure altitude ................................................1750 Feet
• Temperature ................................................25 C (ISA + 13 C)
• Wind component along runway ......................11 knot headwind
• Runway Condition ............................................Dry, level, paved
• Field length .................................................................3000 Feet
March 2010
Information Manual 5-5
Cirrus Design Section 5
SR20 Performance Data
Cruise Conditions:
• Total distance ................................................560 Nautical Miles
• Pressure altitude ........................................................6500 Feet
• Temperature ................................................20 C (ISA + 17 C)
• Expected wind enroute..................................10 Knot Headwind
Landing Conditions:
• Field pressure altitude................................................2000 Feet
• Temperature ................................................20 C (ISA + 10 C)
• Field length.................................................................3000 Feet
Takeoff
The takeoff distance tables, Figure 5-9, show the takeoff ground roll
and horizontal distance to reach 50 feet above ground level. The
distances shown are based on the short field technique.
Conservative distances can be established by reading the tables at the
next higher value of weight, altitude and temperature. For example, in
this particular sample problem, the takeoff distance information
presented for a weight of 3000 pounds, takeoff field pressure altitude
of 2000 feet, and a temperature of 30 C should be used. Using the
conservative values results in the following:
• Ground roll .................................................................1940 Feet
• Total distance to clear a 50-foot obstacle ...................2734 Feet
Since the takeoff distance tables are based upon a zero wind
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：西銳20飛機信息手冊CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(36)