Document ID: chunk:federal_register_of_legislation:F2005B00951:body:0:p3
Version: federal_register_of_legislation:F2005B00951
Segment Type: other
Provision Reference: 
Character Range: 5026–7779

and
 (d) wing flaps in the landing position; and
 (e) centre of gravity in the most unfavourable position within the allowable range; and
 (f) weight used when VSO is being used as a factor to determine compliance with a particular standard.

 (2) The stalling speed, VS1 or minimum steady flight speed, in knots CAS, shall be determined with:
 (a) engine(s) idling with throttle(s) closed; and
 (b) propeller(s) in the take-off position; and
 (c) aeroplane in the configuration relative to the condition in which VS1 is being used; and
 (d) weight used when VS1 is being used as a factor to determine compliance with a particular standard.

 (3) VSO and VS1 shall be established by flight test in accordance with the following procedures:
 (a) aeroplane trimmed, power off, at 1.5 VS1 or the minimum trim speed, whichever is the higher;
 (b) the aeroplane speed reduced with the elevator control until the speed is slightly above the stalling speed, then the elevator control pulled back so that the rate of speed reduction will not exceed 1 knot per second until stall is produced as shown by an uncontrollable downward pitching motion of the aeroplane, or until the control reaches the stop.
3.6 Take-off distance

 (1) The take-off distance shall be established and shall be the distance required to reach a screen height of 50 feet from a standing start, with:
 (a) engine(s) operating within take-off power limitations; and
 (b) wing flaps in the take-off position; and
 (c) the aeroplane reaching the screen height at a take-off safety speed not less than 1.2 VS1.

 (2) The take-off distance scheduled in the aeroplane flight manual shall be that appropriate to a short dry grass surface.

 (3) The take-off safety speed of not less than 1.2 VS1 shall be based on a stall speed VS1 established for the most critical centre of gravity position within the allowable range.

 (4) Take-off charts, when included in the aeroplane flight manual, shall schedule distances established in accordance with the provisions of this paragraph, factored by 1.15.
3.7 Take-off climb

The steady gradient of climb shall be not less than 8% at sea level pressure altitude and a temperature of 15C, and shall be established under the following conditions:
 (a) maximum take-off weight;
 (b) climb speed equal to the take-off safety speed;
 (c) landing gear extended;
 (d) wing flaps in the take-off position.
3.8 Baulked landing climb

 (1) The steady gradient of climb shall be not less than 4% at sea level pressure altitude and a temperature of 15C; and shall be established under the following conditions:
 (a) maximum landing weight;
 (b) climb speed not to exceed the approach speed;
 (c) engine(s) operating within take-off power limitations;
 (d) landing