Federal Aviation Regulations
Sec. 29.175 — Demonstration of static longitudinal stability.
(a) Climb. Static longitudinal stability must be shown in the climb condition at speeds from Vy − 10 kt to Vy + 10 kt with—(1) Critical weight;
(2) Critical center of gravity;
(3) Maximum continuous power;
(4) The landing gear retracted; and
(5) The rotorcraft trimmed at Vy.
(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 VHis less than 0.8 VNE, from VH − 10 kt to VH+ 10 kt, with—
(1) Critical weight;
(2) Critical center of gravity;
(3) Power for level flight at 0.8 VNEor VH, whichever is less;
(4) The landing gear retracted; and
(5) The rotorcraft trimmed at 0.8 VNEor VH, whichever is less.
(c) V
(1) Critical weight;
(2) Critical center of gravity;
(3) Power required for level flight at V
(4) The landing gear retracted; and
(5) The rotorcraft trimmed at VNE− 10 kt.
(d) Autorotation. Static longitudinal stability must be shown in autorotation at—
(1) Airspeeds from the minimum rate of descent airspeed − 10 kt to the minimum rate of descent airspeed + 10 kt, with—
(i) Critical weight;
(ii) Critical center of gravity;
(iii) The landing gear extended; and
(iv) The rotorcraft trimmed at the minimum rate of descent airspeed.
(2) Airspeeds from the best angle-of-glide airspeed − 10kt to the best angle-of-glide airspeed + 10kt, with—
(i) Critical weight;
(ii) Critical center of gravity;
(iii) The landing gear retracted; and
(iv) The rotorcraft trimmed at the best angle-of-glide airspeed.
[Amdt. No. 29–51, 73 FR 11001, Feb. 29, 2008]
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