27.49—Performance at minimum operating speed.
(1)
The hovering ceiling must be determined over the ranges of weight, altitude, and temperature for which certification is requested, with—
(i)
For reciprocating engine powered helicopters, 4,000 feet at maximum weight with a standard atmosphere;
(ii)
For turbine engine powered helicopters, 2,500 feet pressure altitude at maximum weight at a temperature of standard plus 22 °C (standard plus 40 °F).
(3)
The out-of-ground effect hovering performance must be determined over the ranges of weight, altitude, and temperature for which certification is requested, using takeoff power.
(b)
For rotorcraft other than helicopters, the steady rate of climb at the minimum operating speed must be determined over the ranges of weight, altitude, and temperature for which certification is requested, with—