32-02. PERFORMANCE CLASS B – SINGLE-ENGINE AEROPLANES
All questions: 51
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1. On a reciprocating single-engined aeroplane, with increasing altitude at constant gross mass, angle of attack and configuration, the drag:
2. (Refer to figure 032-15)
Using the Power Setting Table, for the single engine aeroplane, determine the cruise TAS and fuel flow (Ibs/hrs) with full throttle and cruise lean mixture in the following conditions, given:
OAT: 3 °C, Pressure altitude: 6.000 ft
Power: Full throttle (21,0 in/Hg. and 2.100 RPM)
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3. The maximum indicated air speed of a piston engined aeroplane, in level flight, is reached:
4. An aircraft is scheduled for takeoff, and requires 800 m (TODR) under normal conditions at ISA seal level. The following airfield characteristics need to be taken into account: Pressure Altitude 2.000 ft, QNH 1.013 hPa, Temperature +21°C, 5 kts tailwind, 2% downslope. Adjust the TODR accordingly using the following factors:
Pressure altitude: ±20 ml 1.000 ft, Runway slope: ±15 m 11% slope
Headwind: -5m/1 kts, Tailwind: +10 m /1 kts
Temperature: +5m/1″ ISA Deviation
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5. For an aeroplane in Performance Class B the net takeoff flight path begins at a height of and ends at a height of .
