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Refer to figures.
An extract of the flight manual of a single engine propeller aircraft is reproduced in the diagram. Given the following conditions:

OAT: +18°C
Aerodrome Pressure Altitude: 1 500 ft
Aeroplane Mass: 1 270 kg
Wind Component: 10 kts tailwind
Runway Surface: Hard, Dry
Runway Slope: 0%

The approximate take-off distance to 50 ft is:

  • A
    690 m
  • B
    395 m
  • C
    465 m
  • D
    550 m
Refer to figure.
On the chart, Mass is in Pounds (lb). Therefore, we must convert 1 270 kg into lb:
  • Kilograms (kg) to Pounds (lb) kg x 2.205 = lb
    1270 kg x 2.205 = 2800 lb

(1) Enter the graph at the bottom left at a temperature of +18ºC. Continue vertically up until intersecting the 1500 ft Pressure Altitude reference line. From this intersection, continue horizontally to the right until the "REFERENCE LINE".
(2) Apply the Mass correction, by drawing a diagonal line down and to the right until a mass of 2800 lb. Continue horizontally to the right until the wind reference line.
(3) Apply the wind correction of 10 kts tailwind by drawing a diagonal line down and to the right. Now, with a horizontal line, continue to the right.
(4) Apply the "Obstacle Height 50 ft" correction by drawing a diagonal line up and to the right following the reference lines (not that these slightly widen up towards the end). Read a result of approximately 1850 ft.
  • Options are in metres, we must convert 1850 ft into metres to find the closest option:
    1850 ft / 3.27 = approx. 566 m
    Closest option: 550 m

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