ED Decision 2003/18/RM
(a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). Unless otherwise provided, prescribed loads are limit loads.
(b) Unless otherwise provided, the air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass in the aeroplane. These loads must be distributed to conservatively approximate or closely represent actual conditions.
(c) If deflections under load would significantly change the distribution of external or internal loads, this redistribution must be taken into account.
(d) Simplified structural design criteria given in this Subpart C and its appendices may be used only for aeroplanes with conventional configurations. If Appendix A is used, the entire appendix must be substituted for the corresponding paragraphs of this subpart, i.e. CS-VLA 321 to 459.
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