(c) Surface loading conditions. Each surface loading condition must be investigated as follows: (1) Simplified limit surface loadings and distributions for the horizontal tail, vertical tail, aileron, wing flaps, and trim tabs are specified in Table 2 and figures 5 and 6 of this Appendix. If more than one distribution is given, each distribution must be investigated. (2) If certification in the acrobatic category is desired, the horizontal tail must be investigated for an unsymmetrical load of 100 percent won one side of the airplane centerline and 50 percent on the other side of the airplane centerline. (d) Outboard fins. Outboard fins must meet the requirements of § 23.455. (e) Special devices. Special devices must meet the requirements of § 23.459. A23.13 Control system loads. (a) Primary flight controls and systems. Each primary flight control and system must be designed as follows: (1) The flight control system and its supporting structure must be designed for loads corresponding to 125 percent of the computed hinge moments of the movable control surface in the conditions prescribed in A23.11 of this Appendix. In addition (1) The system limit loads need not exceed those that could be produced by the pilot and automatic devices operating the controls; and (ii) The design must provide a rugged system for service use, including jamming, ground gusts, taxiing downwind, control inertia, and friction. (2) Acceptable maximum and minimum limit pilot forces for elevator, aileron, and rudder controls are shown in the table in 23.397(b). These pilots loads must be as sumed to act at the appropriate control grip or pads as they would under flight cond tions, and to be reacted at the attachment of the control system to the control surfa horn. (b) Dual controls. If there are dual con trols, the systems must be designed for pilo operating in opposition, using individu pilot loads equal to 75 percent of those o tained in accordance with paragraph (a)| this section, except that individual pil loads may not be less than the minimu limit pilot forces shown in the table § 23.897(b). (c) Ground gust conditions. Ground gu conditions must meet the requirements § 23.415. (d) Secondary controls and systems. Se ondary controls and systems must meet t requirements of § 23.405. TABLE 1-LIMIT FLIGHT LOAD FACTOR |