(2) 2.0 VSO, where VSO is the computed stalling speed with wing flaps fully extended at the maximum weight. 5.2.4.3 Design Cruising Speed, VC – (1) VC in knots may not be less than 4.77 x √(W/S); and (2) VC need not be greater than 0.9 VH at sea level. 4.6 5.2.4.4 Design Dive Speed, VD: VD = 1.4 x VC min where: VC min = required minimum cruising speed. 4.7 5.2.5 Limit Maneuvering Load Factors: – 5.2.5.1 The positive limit maneuvering load factor n1 may not be less than 4.0. 6 5.2.5.2 The negative limit manouevring load factor n2 may not be greater than −2.0. 6 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. 6 5.2.5.4 Loads with speed control devices: Not applicable 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. 6.1 Table 1 – Requirements Design Airspeeds This chapter defines the operating and design airspeeds as required for certification . Maximum speed in level flight VH According to flight tests at maximum weight and maximum continuous power at sea level conditions, the maximum speed in level flight has been determined: Stall speeds VS, VS0, VS1 These speeds will be verified by flight test according to requirement 4.4.1 . In order to calculate the stall speed, the maximum lift coefficient of the aeroplane as a whole is determined first.
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.