32-02. PERFORMANCE CLASS B – SINGLE-ENGINE AEROPLANES
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1. (Refer to figure 032-02)
With regard to the takeoff performance chart for the single engine aeroplane determine the takeoff distance to a height of 50 ft. Given:
OAT: -7 °C
Pressure Altitude: 7.000 ft, Aeroplane Mass: 2.950 lbs
Headwind component: 5 kts, Flaps: Approach setting
Runway: Tarred and Dry
2. (Refer to figure 032-04)
Accounting for the following, what would be the minimum required headwind component for landing? Use the attached chart.
Factored landing distance: 1.300 ft
Temperature at MSL: ISA, Landing Mass: 3.200 lbs
3. (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)
4. A climb gradient required is 3,3%. For an aircraft maintaining 100 kts TAS (no wind), this climb gradient corresponds to a rate of climb (ROC) of approximately:
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:
Pressure Altitude: 4.000 ft, Headwind Component: 15 kts
Flaps: 10°. Runway: 2.000 ft length; tarred and dry
Obstacle Height: 50 ft