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

Critical weight;

Critical center of gravity;

Maximum continuous power;

The landing gear retracted; and

The rotorcraft trimmed at Vy.

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—

Critical weight;

Critical center of gravity;

Power for level flight at 0.8 VNE or VH, whichever is less;

The landing gear retracted; and

The rotorcraft trimmed at 0.8 VNE or VH, whichever is less.

V NE. Static longitudinal stability must be shown at speeds from VNE − 20 kt to VNE with—

Critical weight;

Critical center of gravity;

Power required for level flight at VNE − 10 kt or maximum continuous power, whichever is less;

The landing gear retracted; and

The rotorcraft trimmed at VNE − 10 kt.

Autorotation. Static longitudinal stability must be shown in autorotation at—

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

Critical weight;

Critical center of gravity;

The landing gear extended; and

The rotorcraft trimmed at the minimum rate of descent airspeed.

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

Critical weight;

Critical center of gravity;

The landing gear retracted; and

The rotorcraft trimmed at the best angle-of-glide airspeed.