Compliance statements Compliance statements are shown below: Requirement Subject reference 5.1.1.1 Strength requirements are specified in terms of limit loads (the maximum loads to CS-LSA be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of F2245-12d safety). Unless otherwise provided, prescribed loads are limit loads. 5.1.1.1 Calculated loads are limit loads. See chapter 6. Statement of compliance Requirement Subject reference 5.1.1.2 Unless otherwise provided, the air, ground, and water loads must be placed in CS-LSA equilibrium with inertia forces, considering each item of mass in the airplane. These loads F2245-12d must be distributed to conservatively approximate or closely represent actual conditions. 5.1.1.2 Calculations are based on equilibrium of air and inertia forces. Statement of Mass distribution is taken into consideration. See chapters 6.1, 6.2, 6.4 . compliance Requirement Subject reference 5.1.1.3 The simplified structural design criteria given in Appendix X1 may be used for CS-LSA airplanes with conventional configurations. If Appendix X1 is used, the entire appendix F2245-12d must be substituted for the corresponding paragraphs of this subpart, that is, 5.2.1 to 5.1.1.4 5.7.3. Appendix X2 contains acceptable methods of analysis that may be used for compliance with the loading requirements for the wings and fuselage. The simplified design criteria is not used. Statement of compliance Requirement Subject reference 5.2.1.1 Flight load factors, n, represent the ratio of the aerodynamic force component CS-LSA (acting normal to the assumed longitudinal axis of the airplane) to the weight of the F2245-12d airplane. A positive flight load factor is one in which the aerodynamic force acts upward, 5.2.1.1 with respect to the airplane. The requirement has been met. This is shown in chapter 6.4.5. Statement of compliance Requirement Subject reference 5.2.1.2 Compliance with the flight load requirements of this section must be shown at CS-LSA each practicable combination of weight and disposable load within the operating F2245-12d limitations specified in the POH. 5.2.1.2 Every combination of weight and centre of gravity was considered. See chapter 6. Statement of compliance
Compliance statements Compliance statements are shown below: Requirement reference Subject CS-LSA F2245-12d 5.1.1.1 5.1.1.1 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. Statement of compliance Calculated loads are limit loads. See chapter 6. Requirement reference Subject CS-LSA F2245-12d 5.1.1.2 5.1.1.2 Unless otherwise provided, the air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass in the airplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Statement of compliance Calculations are based on equilibrium of air and inertia forces. Mass distribution is taken into consideration. See chapters 6.1, 6.2, 6.4 . Requirement reference Subject CS-LSA F2245-12d 5.1.1.4 5.1.1.3 The simplified structural design criteria given in Appendix X1 may be used for airplanes with conventional configurations. If Appendix X1 is used, the entire appendix must be substituted for the corresponding paragraphs of this subpart, that is, 5.2.1 to 5.7.3. Appendix X2 contains acceptable methods of analysis that may be used for compliance with the loading requirements for the wings and fuselage. Statement of compliance The simplified design criteria is not used. Requirement reference Subject CS-LSA F2245-12d 5.2.1.1 5.2.1.1 Flight load factors, n, represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of the airplane) to the weight of the airplane. A positive flight load factor is one in which the aerodynamic force acts upward, with respect to the airplane. Statement of compliance The requirement has been met. This is shown in chapter 6.4.5. Requirement reference Subject CS-LSA F2245-12d 5.2.1.2 5.2.1.2 Compliance with the flight load requirements of this section must be shown at each practicable combination of weight and disposable load within the operating limitations specified in the POH. Statement of compliance Every combination of weight and centre of gravity was considered. See chapter 6.
ABCD-FL-57-00%20-%20Wing%20Load%20Calculation%20-%20v1%2008.03.16.docx