ED Decision 2003/18/RM
(a) If flaps or similar high lift devices to be used for take-off, approach, or landing are installed, the aeroplane, with the flaps fully deflected at VF, is assumed to be subjected to symmetrical manoeuvres and gusts resulting in limit load factors within the range determined by -
(1) Manoeuvring to a positive limit load factor of 2·0; and
(2) Positive and negative gust of 7·62 m/s acting normal to the flight path in level flight.
(b) VF must be assumed to be not less than 1·4 VS or 1·8 VSF, whichever is greater, where -
VS is the computed stalling speed with flaps retracted at the design weight; and
VSF is the computed stalling speed with flaps fully extended at the design weight.
However, if an automatic flap load limiting device is used, the aeroplane may be designed for the critical combinations of airspeed and flap position allowed by that device.
(c) In designing the flaps and supporting structures the following must be accounted for:
(1) A head-on gust of 7·62 m/s (EAS).
(2) The slipstream effects specified in CS-VLA 457(b).
(d) In determining external loads on the aeroplane as a whole, thrust, slipstream, and pitching acceleration may be assumed to be zero.
(e) The requirements of CS-VLA 457, and this paragraph may be complied with separately or in combination.
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