32-02. PERFORMANCE CLASS B – SINGLE-ENGINE AEROPLANES
All questions: 51
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1. What margin above the stall speed is provided by the landing reference speed VREF?
2. If a TOD of 800 m is calculated at sea level, on a level, dry runway, with standard conditions and with no wind, what would the TOD be for the conditions listed below?
Airfield elevation: 2.000 ft
QNH: 1.013,25 mb
Temperature: 21 °C
Wind: 5 kts tailwind
Dry runway with a 2% up slope (Assuming: ±20 m per 1.000 ft elevation; +10 m per 1 kts of reported tailwind; ±5 m per 1°C ISA deviation and ±5% 11% slope)
3. The landing reference speed VREF has, in accordance with international requirements, the following margins above stall speed in landing configuration:
4. (Refer to figure 032-04)
With regard to the landing chart for the single engine aeroplane determine the landing distance from a height of 50 ft. Given:
OAT: 0″C
Pressure Altitude: 1.000 ft
Aeroplane Mass: 3.500 lbs
Tailwind component: 5 kts
Flaps: Landing position (down)
Runway: Tarred and Dry
5. (Refer to figure 032-02)
With regard to the takeoff performance chart for the single-engine aeroplane, determine the maximum allowed takeoff weight, given:
OAT: ISA
Pressure Altitude: 4.000 ft
Headwind Component: 15 kts
Flaps: 10°
Runway: 2.000 ft length; tarred and dry
Obstacle Height: 50 ft
