Text in force at CAR3R-8: from CAR3R-5, effective 1 Oct 1959. OCR text
(a) Three-control airplanes.
(1) The static directional stability, as shown by the tendency to recover from a skid with rudder free, shall be positive for all land. ing gear and flap positions appropriate to the takeoff, climb, cruise, and approach configurations, with symmetrical power up to maximum continuous power, and at all speeds from 1.2Vs, up to the maxi. mum permissible speed for the configuration being investigated. The angle of skid for these tests shall be appropriate to the type of airplane. At greater angles of Skid up to that at which full rudder is employed or a control force limit specified in § 3.106 is obtained, whichever occurs first, and at speeds from 1.2Vs, t0 Vp, the rudder pedal force shall not reverse, (2) The static lateral Stability, as shown by the tendency to raise the low wing in a sideslip, shall be positive for all landing gear and flap positions with Symmetrical power up to 75 percent maximum continuous power at all speeds above 1.2Vs, up to the maximum permissible speed for the configuration investigated but shall not be negative at a Speed of 1.2Vs,. The angle of sideslip for these tests shall be appropriate to the type of airplane but in no case shall the sideslip be less than that obtained with 10 .degrees of bank. (3) In straight steady sideslips at a speed of 1.2Vs, for all gear and flap positions and for all symmetrical power conditions up to 50 percent maximum continuous power, the aileron and rudder control movements and forces Shall increase steadily, but not necessarily in constant proportion, as the angle of sideSlip is increased up to the maximum appropriate to the type of airplane. At greater angles up to that at which the full rudder or aileron control is employed or a control force limit specified by § 3.106 is obtained, the rudder pedal force shall not reverse. Sufficient bank shall accompany sideslipping to prevent departure from a constant heading. Rapid entry into or recovery from a maximum Sideslip shall not result in uncontrollable flight characteristics, : 7. By amending $3.120(e) (1) to read as follows:
(Secs. 313(a), 601, 608, 72 Stat. 752, 775, 776; 49 U.S.C. 1354(a), 1421, 1423) ·