MOC VTOL.2200 Structural design envelope

The following design values and limitations should be established to show compliance with the structural requirements of this Subpart, for each aircraft configuration or flight mode, as appropriate:

(Note: Failure conditions need not be taken into account when defining these design values and limitations.)

(a)     The design maximum and design minimum weights.

(b)     The lift/thrust units design rpm ranges with power on and power off, if applicable. These design values should provide adequate margin to accommodate the variations in rpm speed occurring in any manoeuvre.

(c)      Design Airspeeds:

(3)     Maximum level flight speed, V_H. The maximum level flight speed at maximum continuous power;

(4)     Maximum Design speed, V_D.

(5)     Never-Exceed speed, V_NE.  V_NE should not be greater than 0.9 times V_D.

(6)     Velocity of Normal Operations, V_NO is the maximum structural cruising speed. V_NO should be defined by the applicant and should be less than or equal to V_H and V_NE

(7)     Maximum design rearward and sideward flight speeds.  The maximum design rearward and sideward speeds should be defined to be no less than 1.11 times the maximum permitted rearward and sideward speeds.

(8)     Design speed for maximum gust intensity, V_B (for Category Enhanced). For V_B, the following applies:

(A)     V_B should not be less than the speed determined by the intersection of the line representing the maximum positive lift C_{N MAX} and the line representing the rough air gust velocity on the gust V-n diagram, or V_S1√n_g , whichever is less, where –

(a)     n_g the positive aircraft gust load factor due to gust, at speed V_NO, and at the particular weight under consideration; and

(b)     V_S1 is the stalling speed with the flaps retracted at the particular weight under consideration.

(B)     V_B need not be greater than V_NO.

(C)     If loss of control due to stall is not possible, or definition of V­_B in accordance with (A) is not applicable, V_B should be defined according to the VTOL operating limit for flight in turbulent conditions.

(d)     The centre of gravity limits corresponding to the configuration of the aircraft.

(e)     The rotational speed ratios between each lift/thrust unit and each connected rotating component, as applicable.

(f)      The positive and negative limit manoeuvring load factors should be defined based on the maximum capability of the aircraft, taking into account the flight control system (without failure cases), for which:

(9)     The probability of being exceeded is shown by analysis to be extremely improbable within the design altitude and temperature range;

(10)    The selected values are appropriate to each weight condition between design maximum and minimum weights and associated critical centres of gravity; and

(11)    The positive load factor is not less than 2.0 and the negative limit manoeuvring load factor is not less than -0.5.

Note: An absolute maximum positive and negative limit manoeuvring load factor may be proposed for acceptance by the Agency, as appropriate for the aircraft operation and consistent with current Certification Specifications (e.g. CS 23.337 and CS 27.337).

(g)     Ranges of altitudes and temperature for which certification is requested.

(h)     Ranges of position of adjustable elements of lift/thrust units and control devices, if applicable.