§3.216 Maneuvering loads.

(a) At maneuvering speed Vp assume a sudden deflection of the elevator control to the maximum upward deflection as limited by the control stops or pilot effort, whichever is critical. Note: The average loading of Figure 3-3 and the distribution of Figure 3-8 may be used. In determining the resultant normal force coefficient for the tail under these conditions, it will be permissible to assume that the angle of attack of the stabilizer with respect to the resultant direction of air flow is equal to that which occurs when the airplane is in steady unaccelerated flight at a flight speed equal to Vp. The maximum elevator deflection can then be determined from the above criteria and the tail normal force coefficient can be obtained from the data given in NACA Report No. 688, "Aerodynamic Characteristics of Horizontal Tail Surfaces," or other applicable NACA reports. (b) Same as case (a) except that the elevator deflection is downward. Note: The average loading of Figure 3-3 and the distribution of Figure 3-8 may be used. (c) At all speeds above Vp the horizontal tail shall be designed for the maneuvering loads resulting from a sudden upward deflection of the elevator, followed by a downair deflection of the elevator such that the following combinations of normal acceleration and angular acceleration are obtained: Condition Airplane normal acceleration n Angular acceleration radian/sec.2 Down load 1.0 Up load nm ‘| ‘| ‘| ‘| ‘| ‘| Acceptable values of limit average maneuvering control surface loadings can be obtained from Figure 3-3 (b) as follows: HORIZONTAL TAIL SURFACES (1) Condition § 3.216 (a): Obtain as function of W/S and surface deflection; Use Curve C for deflection 10° or less; Use Curve B for deflection 20°; Use Curve A for deflection 30° or more; (Interpolate for other deflections); Use distribution of Figure 3-8. (2) Condition § 3.216 (b): Obtain from Curve B. Use distribution of Figure 3-8. VERTICAL TAIL SURFACES (3) Condition § 3.219 (a): Obtain as function of W/S and surface deflection in same manner as outlined in (1) above, use distribution of Figure 3-8; (4) Condition § 3.219 (b): Obtain from Curve C, use distribution of Figure 3-7; (5) Condition § 3.219 (c): Obtain from Curve A, use distribution of Figure 3-9. (Note that condition § 3.220 generally will be more critical than this condition.) AILERONS (6) In lieu of conditions § 3.222 (b): Obtain from Curve B, acting in both up and down directions. Use distribution of Figure 3-10. where: FIG. 2-31a)-—-LIMIT AVERAGE MANELIVERING CONTROL SURFACE LOADINGS aad UMITAVERAGE MANEUVERING LOADING 3 45 SW RG gy EPSP] WHERE = FS THE POSITIVE LIMIT MANEUVERING LOAT 4 ao | PAC TOR WAgD ik BESIGIC. = 4 Sh oware: Ee 1 = W SHALL NOT BE LESS THAN : 307 42PSFINANYCASE, -LaB:raea te 2s - ata <t7 a ® oF ana x tr 4 3 10> F $= * o£ = c 5 ro 18 20 Wipsr FIGURE 3-3(b} —LIMIT AVERAGE MANEUVERING CONTROL SURFACE LOADING nm = positive limit maneuvering load factor used in the design of the airplane. V = initial speed in miles per hour. MCREMENT EGHY LHAtTMANEUVERINGTALLOAD|DESIGNW LiW * r > x 3 . > : OVERALL LENGTH OF AIRPLANE {FT} DESIGN SPEER ter} FIG. 3-4 —— MANEUVERING TA LOAD WOREMENT iP OR DOWN] + a \ N \ *AVERAGEpowGUSTLOADING47SF} a SSSSERSeTesTeeeeerot a. & * v we° S-1PSF} FIG, 3-5{2}—DOWN GUST LOATING GN HORIZONTAL TATL SURFACE 7 i ¥ ] | ERLIDIEUEIEELELIFibs & WAVERAGEUPGUSTLOADING[PSF)co TEVTATET , o w = {PSF} FIG, 3-5{b)—UP GUST LOADING ON HORIZONTAL TAIL SURFACE TETTITIGTaa Yeu 209 a aan 160 _ 4 Pans > aa 140 3 = 20k + a a ita = a nn In 5 be 4 , s i 20 — ‘6 : oO oF ——. E Oo & MOTE; THESE CURVES age = = OF FOR ASPECT RATIO R +35. FOR uo OTHER ASPECT RATS = > & WVUTIPLY LOADINGS . a oF er “ F ok p fos fp ti, pe) yt o % 46 &6 r7) 130 20 140 W MAXIMUM WEIGHT ‘Sy ” AREA OF VERTIGAL WML SURFACE FIG. 3- ~~ 496 “EO ae ! CASTING Ita OrRECTION OPPOSTE 3 TO THE STaBst eh joant Lg won M BALABCING CompeTaeg 23.22rF Pe40% OF NET GALANCING EGAD (FLAPS REYHaCTEO} P*O (FLAPS DEFLECTED) ip) FN COMOCTEON OS2721 fet 20, OF ME? Tat LOAD FIG, 3-7 TAIL SURFAGE LOAD DISTRIBUTION FIG, 3-8 TASL' SURFACE WOAG DISTRIBUTION (d) The total tail load for the conditions specified in (c) shall be the sum of: (1) The balancing tail load corresponding with the condition at speed V and the specified value of the normal load factor n, plus (2) the maneuvering load increment due to the specified value of the angular acceleration. ZN =O 4 ALAS1a, ¢{— WR Tp ) it NOTE: The maneuvering load increment of Figure 3-4 and the distributions of Figure 3-8 (for downloads) and Figure 3-9 (for uploads) may be used. These distributions apply to the total tail load.