Commission Regulation (EC) No 8/2008 of 11 December 2007 amending Council Regulation (EEC) No 3922/91 as regards common technical requirements and administrative procedures applicable to commercial transportation by aeroplane (Text with EEA relevance) (c. 8)

ANNEX

“Appendix 1 to OPS 1.525 (b) General — Take-off and Landing Climb

(a)

Take-off Climb

(1)

All Engines Operating

(i)

The steady gradient of climb after take-off must 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 7 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 and 1,2 VS1.

(2)

One Engine Inoperative

(i)

The steady gradient of climb at an altitude of 400 ft above the take-off surface must 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 must 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 must be at least 2,5 % with:

(A)

Not more than the power or thrust that is available 8 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.

(2)

One engine Inoperative

(i)

The steady gradient of climb must 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.”