AMC VLA 441 Manoeuvring Loads (Interpretative Material and Acceptable Means of Compliance)

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

AMC VLA 441 Manoeuvring Loads (Interpretative Material and Acceptable Means of Compliance) ED Decision 2003/18/RM For aeroplanes where the horizontal tail is supported by the vertical tail, the tail surfaces and their supporting structure including the rear portion of the fuselage should be designed to withstand the prescribed loadings on the vertical tail and the roll-moments induced by the horizontal tail acting in the same direction. 2 For T-tails in the absence of a more rational analysis, the rolling moment induced by deflection of the vertical rudder may be computed as follows:  <table border="0" cellpadding="0" cellspacing="0" width="573"><tr><td colspan="3" valign="top" width="573"><p>where -</p></td></tr><tr><td valign="top" width="35"><p>M_r</p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>induced roll-moment at horizontal tail (Nm) </p></td></tr><tr><td valign="top" width="35"><p>b_H</p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>span of horizontal tail (m) </p></td></tr><tr><td valign="top" width="35"><p>ß </p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>angle of zerolift line due to rudder deflection </p></td></tr><tr><td valign="top" width="35"><p>ß </p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p><div class="image-container"><img alt="EASA EAR image" src="/static/files/file_CbObCD5goL3/image041.jpg"/></div> ηf_η</p></td></tr><tr><td valign="top" width="35"><p>η </p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>rudder deflection </p></td></tr><tr><td valign="top" width="35"><p><div class="image-container"><img alt="EASA EAR image" src="/static/files/file_CbObCD5goL3/image043.jpg"/></div></p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>change of zerolift angle of ηfη = 1 </p></td></tr><tr><td valign="top" width="35"><p>f_η</p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>effectivity factor in accordance with angle of rudder deflection</p></td></tr><tr><td valign="top" width="35"><p>V </p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>speed of flight (m/s) </p></td></tr><tr><td valign="top" width="35"><p>S_t</p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>area of horizontal tail (m²) </p></td></tr><tr><td valign="top" width="35"><p>ρ_ο</p></td><td valign="top" width="16"><p>= </p></td><td valign="top" width="523"><p>air density at sea level (kg/m³) </p></td></tr></table>