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Refer to figure.
Given:

Gear and flaps: retracted
Gross mass: 8 200 lbs
Altitude: 6 000 ft
OAT: +10°C
QNH: 1030 hPa
Find the rate of climb for a twin-engine aeroplane climbing with maximum climb power in still air:
  • A
    2 680 ft/min
  • B
    2 250 ft/min
  • C
    2 500 ft/min
  • D
    2 370 ft/min

Refer to figure.

The Pressure Altitude (Pressure reference 1013 hPa) must be calculated to enter the graph:
Assuming 1 hPa = 30 ft

  • 1030 hPa - 1013 hPa = 17 hPa
    17 hPa x 30 ft/hPa = 510 ft
    When the altimeter setting is reduced, the altimeter reading will also decrease:
    PA = 6000 ft - 510 ft = 5490 ft (approx. 5500 ft)
(1) Enter the graph at the bottom left at a temperature of +10ºC.
(2) Draw a vertical line up to the imaginary reference line of approximately 5500 ft Pressure altitude.
(3) Continue horizontally to the right until the "Reference Line". Adjust for a mass of 8200 lb by continuing diagonally up and to the right.
(4) From this point, continue horizontally to the right and read a result of approx. 2370 ft/min.

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