Requirement Subject reference 5.2.4.4 Design Dive Speed, VD: CS-LSA VD = 1.4 x VC min where: VC min = required minimum cruising speed. F2245-12d 5.2.4.4 The requirement has been met. This is shown in chapter 4.7. Statement of compliance Requirement Subject reference 5.2.5.1 The positive limit maneuvering load factor n1 may not be less than 4.0. CS-LSA 5.2.5.1 The requirement has been met. This is shown in chapter 6. Statement of compliance Requirement Subject reference 5.2.5.2 The negative limit maneuvering load factor n2 may not be greater than −2.0. CS-LSA F2245-12d 5.2.5.2 The requirement has been met. This is shown in chapter 6. Statement of compliance Requirement Subject reference 5.2.5.3 Loads with wing flaps extended: CS-LSA (1) if flaps or other similar high lift devices are used, the airplane must be designed for n1 = 2.0 with the flaps in any position up to VF; and 5.2.5.3 (2) n2 = 0. The requirement has been met. This is shown in chapter 6. Statement of compliance Requirement Subject reference Gust Load Factors The airplane must be designed for the loads resulting from: – CS-LSA The gust velocities specified in 5.2.3.3 with flaps retracted, and F2245-12d Positive and negative gusts of 7.5 m/s (24.6 ft/s) nominal intensity at VF with the flaps 5.2.6 fully extended. 5.2.6.1 NOTE 4 In the absence of a more rational analysis, the gust load factors may be – 5.2.6.2 computed by the method of Appendix X3. The requirement has been met. This is shown in chapter 6.1. Statement of compliance
Requirement reference Subject CS-LSA F2245-12d 5.2.4.4 5.2.4.4 Design Dive Speed, VD: VD = 1.4 x VC min where: VC min = required minimum cruising speed. Statement of compliance The requirement has been met. This is shown in chapter 4.7. Requirement reference Subject CS-LSA 5.2.5.1 5.2.5.1 The positive limit maneuvering load factor n1 may not be less than 4.0. Statement of compliance The requirement has been met. This is shown in chapter 6. Requirement reference Subject CS-LSA F2245-12d 5.2.5.2 5.2.5.2 The negative limit maneuvering load factor n2 may not be greater than −2.0. Statement of compliance The requirement has been met. This is shown in chapter 6. Requirement reference Subject CS-LSA 5.2.5.3 5.2.5.3 Loads with wing flaps extended: (1) if flaps or other similar high lift devices are used, the airplane must be designed for n1 = 2.0 with the flaps in any position up to VF; and (2) n2 = 0. Statement of compliance The requirement has been met. This is shown in chapter 6. Requirement reference Subject CS-LSA F2245-12d 5.2.6 5.2.6.1 5.2.6.2 Gust Load Factors – The airplane must be designed for the loads resulting from: The gust velocities specified in 5.2.3.3 with flaps retracted, and Positive and negative gusts of 7.5 m/s (24.6 ft/s) nominal intensity at VF with the flaps fully extended. NOTE 4 – In the absence of a more rational analysis, the gust load factors may be computed by the method of Appendix X3. Statement of compliance The requirement has been met. This is shown in chapter 6.1.
ABCD-FE-01-00%20Flight%20Envelope%20-%20v1%2008.03.16.docx