CS-VLA 397 Limit control forces and torques

• ED Decision 2003/18/RM found in: CS-VLA Amdt 1 - Very Light Aeroplanes (Mar 2009)

CS-VLA 397 Limit control forces and torques ED Decision 2003/18/RM (a) In the control surface flight loading condition, the airloads on movable surfaces and the corresponding deflections need not exceed those that would result in flight from the application of any pilot force within the ranges specified in subparagraph (b) of this paragraph. In applying this criterion the effects of tabs must be considered. (b) The limit pilot forces and torques as follows: <table border="0" cellpadding="0" cellspacing="0" width="567"><tr><td width="217"><p>Control </p></td><td valign="top" width="175"><p>Maximum forces or torques in daN (D=wheel diameter) </p></td><td valign="top" width="175"><p>Minimum </p><p>forces or torques </p></td></tr><tr><td valign="top" width="217"><p>Aileron:</p></td><td valign="top" width="175"></td><td valign="top" width="175"></td></tr><tr><td valign="top" width="217"><p> Stick</p></td><td valign="top" width="175"><p>30</p></td><td valign="top" width="175"><p>17·8</p></td></tr><tr><td valign="top" width="217"><p> Wheel*</p></td><td valign="top" width="175"><p>22.2 D (mdaN)</p></td><td valign="top" width="175"><p>17.8 D (mdaN)</p></td></tr><tr><td valign="top" width="217"><p>Elevator:</p></td><td valign="top" width="175"></td><td valign="top" width="175"></td></tr><tr><td valign="top" width="217"><p> Stick</p></td><td valign="top" width="175"><p>74</p></td><td valign="top" width="175"><p>44.5 </p></td></tr><tr><td valign="top" width="217"><p> Wheel (symmetrical)</p></td><td valign="top" width="175"><p>89</p></td><td valign="top" width="175"><p>44.5</p></td></tr><tr><td valign="top" width="217"><p> Wheel (unsymmetrical)*</p></td><td valign="top" width="175"><p>-------</p></td><td valign="top" width="175"><p>44.5</p></td></tr><tr><td valign="top" width="217"><p>Rudder</p></td><td valign="top" width="175"><p>89</p></td><td valign="top" width="175"><p>58</p></td></tr></table> \*The critical parts of the aileron control system must also be designed for a single tangential force with a limit value of 1.25 times the couple force determined from the above criteria. (c) The rudder control system must be designed to a load of 100 daN per pedal, acting simultaneously on both pedals in forward direction.