ED Decision 2003/18/RM
(a) General. Compliance with the strength requirements of this subpart must be shown at any combination of airspeed and load factor on and within the boundaries of a flight envelope (similar to the one in sub-paragraph (d) of this paragraph) that represents the envelope of the flight loading conditions specified by the manoeuvring and gust criteria of sub-paragraphs (b) and (c) of this paragraph respectively.
(b) Manoeuvring envelope. Except where limited by maximum (static) lift coefficients, the aeroplane is assumed to be subjected to symmetrical manoeuvres resulting in the following limit load factors:
(1) The positive manoeuvring load factor specified in CS-VLA 337 at speeds up to VD;
(2) The negative manoeuvring load factor specified in CS-VLA 337 at VC; and
(3) Factors varying linearly with speed from the specified value at VC to 0.0 at VD.
(c) Gust envelope
(1) The aeroplane is assumed to be subjected to symmetrical vertical gusts in level flight. The resulting limit load factors must correspond to the conditions determined as follows:
(i) Positive (up) and negative (down) gusts of 15·24 m/s at VC must be considered.
(ii) Positive and negative gusts of 7·62 m/s at VD must be considered.
(2) The following assumptions must be made:
(i) The shape of the gust is -
where -
S = distance penetrated into gust (m);
C̅ = mean geometric chord of wing (m); and
Ude = derived gust velocity referred to in sub-paragraph (c)(1) (m/s)
(ii) Gust load factors vary linearly with speed between VC and VD.
(d) Flight envelope
Point G need not be investigated when the supplementary condition specified in CS-VLA 369 is investigated.