1. (a) Climb. Static longitudinal stability must be shown in the climb condition at speeds from Vy − 10 kt to Vy + 10 kt with—

   1. (1) Critical weight;
   2. (2) Critical center of gravity;
   3. (3) Maximum continuous power;
   4. (4) The landing gear retracted; and
   5. (5) The rotorcraft trimmed at Vy.

2. (b) Cruise. Static longitudinal stability must be shown in the cruise condition at speeds from 0.8 VNE−10 kt to 0.8 VNE + 10 kt or, if VH is less than 0.8 VNE, from VH − 10 kt to VH + 10 kt, with—

   1. (1) Critical weight;
   2. (2) Critical center of gravity;
   3. (3) Power for level flight at 0.8 VNE or VH, whichever is less;
   4. (4) The landing gear retracted; and
   5. (5) The rotorcraft trimmed at 0.8 VNE or VH, whichever is less.

3. (c) VNE. Static longitudinal stability must be shown at speeds from VNE − 20 kt to VNE with—

   1. (1) Critical weight;
   2. (2) Critical center of gravity;
   3. (3) Power required for level flight at VNE − 10 kt or maximum continuous power, whichever is less;
   4. (4) The landing gear retracted; and
   5. (5) The rotorcraft trimmed at VNE − 10 kt.

4. (d) Autorotation. Static longitudinal stability must be shown in autorotation at—

   1. (1) Airspeeds from the minimum rate of descent airspeed − 10 kt to the minimum rate of descent airspeed + 10 kt, with—

      1. (i) Critical weight;
      2. (ii) Critical center of gravity;
      3. (iii) The landing gear extended; and
      4. (iv) The rotorcraft trimmed at the minimum rate of descent airspeed.

   2. (2) Airspeeds from the best angle-of-glide airspeed − 10kt to the best angle-of-glide airspeed + 10kt, with—

      1. (i) Critical weight;
      2. (ii) Critical center of gravity;
      3. (iii) The landing gear retracted; and
      4. (iv) The rotorcraft trimmed at the best angle-of-glide airspeed.

[Amdt. 29-51, 73 FR 11001, Feb. 29, 2008]