CAT.POL.A.340 Take-off and landing climb requirements

The operator of a two-engined aeroplane shall fulfil the following take-off and landing climb requirements.

(a)Take-off climb

(1)All engines operating

(i)The steady gradient of climb after take-off shall be at least 4 % with:

(A)take-off power on each engine;

(B)the landing gear extended, except that if the landing gear can be retracted in not more than seven seconds, it may be assumed to be retracted;

(C)the wing flaps in the take-off position(s); and

(D)a climb speed not less than the greater of 1,1 VMC (minimum control speed on or near ground) and 1,2 VS1 (stall speed or minimum steady flight speed in the landing configuration).

(2)OEI

(i)The steady gradient of climb at an altitude of 400 ft above the take-off surface shall be measurably positive with:

(A)the critical engine inoperative and its propeller in the minimum drag position;

(B)the remaining engine at take-off power;

(C)the landing gear retracted;

(D)the wing flaps in the take-off position(s); and

(E)a climb speed equal to that achieved at 50 ft.

(ii)The steady gradient of climb shall be not less than 0,75 % at an altitude of 1 500 ft above the take-off surface with:

(A)the critical engine inoperative and its propeller in the minimum drag position;

(B)the remaining engine at not more than maximum continuous power;

(C)the landing gear retracted;

(D)the wing flaps retracted; and

(E)a climb speed not less than 1,2 VS1.

(b)Landing climb

(1)All engines operating

(i)The steady gradient of climb shall be at least 2,5 % with:

(A)not more than the power or thrust that is available eight seconds after initiation of movement of the power controls from the minimum flight idle position;

(B)the landing gear extended;

(C)the wing flaps in the landing position; and

(D)a climb speed equal to VREF (reference landing speed).

(2)OEI

(i)The steady gradient of climb shall be not less than 0,75 % at an altitude of 1 500 ft above the landing surface with:

(A)the critical engine inoperative and its propeller in the minimum drag position;

(B)the remaining engine at not more than maximum continuous power;

(C)the landing gear retracted;

(D)the wing flaps retracted; and

(E)a climb speed not less than 1,2 VS1.