AMC 22.447(a) Combined loads on tail surfaces

CAA ORS9 Decision No. 1

(1) In the absence of rational data the unsymmetrical distribution shall be obtained by multiplying the air load on one side of the plane of symmetry by (1+x) and on the other side by (1-x).

(2) For point A of the V-n envelope the value of x shall be 0.34 and in the case of an aerobatic category sailplane certificated for flick manoeuvres x shall be 0.5. For point D the value of x shall be 0.15.

(3) The unsymmetrical horizontal tail load must not be combined with the induced rolling moment at the T-tail.