Climb

6. Climb - Landing climb: All-engines-operating. The maximum weight must be determined with the airplane in the landing configuration, for each altitude, and ambient temperature within the operational limits established for the airplane and with the most unfavorable center of gravity and out-of-ground effect in free air, at which the steady gradient of climb will not be less than 3.3 percent, with:
(1) The engines at the power that is available 8 seconds after initiation of movement of the power or thrust controls from the mimimum flight idle to the takeoff position.
(2) A climb speed not greater than the approach speed established under section 7 of this regulation and not less than the greater of 1.05MC or 1.10VS1.
(b) En route climb, one-engine-inoperative.
(1) the maximum weight must be determined with the airplane in the en route configuration, the critical engine inoperative, the remaining engine at not more than maximum continuous power or thrust, and the most unfavorable center of gravity, at which the gradient at climb will be not less than -
(i) 1.2 percent (or a gradient equivalent to 0.20 Vso2, if greater) at 5,000 feet and an ambient temperature of 41 °F. or
(ii) 0.6 percent (or a gradient equivalent to 0.01 Vso2, if greater) at 5,000 feet and ambient temperature of 81 °F.
(2) The minimum climb gradient specified in subdivisions (i) and (ii) of subparagraph (1) of this paragraph must vary linearly between 41 °F. and 81 °F. and must change at the same rate up to the maximum operational temperature approved for the airplane.

Source

14 CFR § SFAR_No_23


Scoping language

None
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