Text in force at CAR3R-8: from CAR3R-7, effective 3 May 1962. OCR text
(a) Multiengine airplanes shall have stall characteristics which preclude unintentional spin entry, These characteristics shall be demonstrated by performing the maneuvers prescribed in paragraph (b) of this section at the lowest practical altitude with: en~ ey (1) The critical engine inoperative and its propeller in the, normal inoperative position; (2) Flaps and landing gear extended, and with flaps retracted and landing gear extended; and (3) The remaining engines operating at full throttle, except that the power need not be greater than maximum continuous power. (bo) After a steady curvilinear flight condition has been established, and while maintaining a 15-degree bank towards in one case, and away in the other ease, from the inoperative engine, the angle of attack shall be steadily increased with the elevator control until an uncontrollable downward pitching motion of the airplane indicates the stall. In performing these maneuvers, the following shall apply: (1) It shall be possible to produce and correct roll by unreversed use of the lateral control until the airplane stalis; (2) It shall be possible to effect immediate recovery to full fiight control with wings level from the stalled condition by normal use of the controls, reducing power on the operating engines if desired without the airplane exceeding a G0-degree bank angle; and (3) The loss of altitude, as measured from the altitude at which the airplane starts to pitch uncontrollably to the altitude, at which level flight is regained, and the pitch angle shall be entered in the performance section of the Airplane Flight Manual for airplanes having a maximum certificated weight of more than 6,000 pounds, or shall be shown on a cockpit placard for airplanes having a maximum certificated weight of 6,000 pounds or less, 7. By amending § 3.124(a) by deleting the first sentence and inserting in lieu thereof ‘‘All single-engine airplanes shall recover from a one-turn spin in not more than one additional turn. The controls shall be applied in the manner normally used for recovery. For both the flaps retracted and flaps extended conditions, the applicable limiting airspeed and postive limit maneuvering load factor shall not be exceeded. For the flaps extended condition, it shall be acceptable to retract the flaps during recovery.” 8. By amending § 3.124(¢) by inserting in the introductory sentence between the words “spinning” and “and” the words “at least six turns’; by deleting from subparagraph (1) the clause “the airplane shall recover from a six-turn spin, or from any point in a six-turn spin,” and inserting in lieu thereof “the airplane shall recover from any point in a spin not exceeding six turns with flaps retracted and one turn with flaps extended;” and by amending subparagraph (2) to read:
section with altitudes from sea level to 8,000 feet and with temperatures at these altitudes from minus 60° F. below standard to plus 40° F, above standard shall be included. § 3.780-2 [Deletion] 60. By deleting § 3.780-1. (Sees. 318(a), 601, 603; 72 Stat. 752, 775, 776; 49 U.S.C, 1354(a), 1421, 1423) Issued in Washington, D.C., on March 27, 1962, N. E. Haasy, Administrator. EPR. Doc. 62-3085; Filed, Apr. 2, 1962; 8:45 a.m.) (As published in the Federal Register Lai FAR. 31607 April 3, 1962) ·