Amdt. 23-48, E.. 03/11/96
FAR 23.345 : High lift devices.
(a)
[If .aps or similar high lift devices are to be used for takeo., approachor landing, the airplane, with the .aps fully extended at VF, is assumed to be subjected to symmetrical maneuvers and gusts within the range determined by–

(1)
Maneuvering, to a positive limit load factor of 2.0; and

(2)
Positive and negative gust of 25 feet per second acting normal to the .ight path in level .ight.

(b)
VF must be assumed to be not less than 1.4 VS or 1.8 VSF, whichever is greater, where–

(1)
VS is the computed stalling speed with .aps retracted at the design weight; and

(2)
VSF is the computed stalling speed with .aps fully extended at the design weight.

(3)
If an automatic .ap load limiting device is used, the airplane may be designed for the critical combinations of airspeed and .ap position allowed by that device.

(c)
In determining external loads on the airplane as a whole, thrust, slipstream, and pitching acceleration may be assumed to be zero.

(d)
The .aps, their operating mechanism, and their supporting structures, must be designedto withstandthe conditionsprescribedinparagraph(a) ofthis section. In addition, with the .aps fully extended at VF, the following conditions, taken separately, must be accounted for :

(1) Ahead-ongusthaving a velocity of25feetper second(EAS), combined with propeller slipstream corresponding to75percent of maximum continuouspo-wer; and

(2)
The e.ects of propeller slipstream corresponding to maximum takeo. power.] Amdt. 23-48, E.. 03/11/96

FAR 23.347 : Unsymmetrical .ight conditions.

(a)
[The airplane is assumed to be subjected to the unsymmetrical .ight conditions of Secs. 23.349 and 23.351. Unbalanced aerodynamic moments about the center of gravity must be reacted in a rational or conservative manner, considering the principal masses furnishing the reacting inertia forces.

(b) Acrobaticcategory airplanescerti.edfor .ick maneuvers(snap roll) mustbedesi-gned for additional asymmetric loads acting on the wing and the horizontal tail.]
Amdt. 23-48, E.. 03/11/96
FAR 23.349 : Rolling conditions.
The wing and wing bracing must be designed for the following loading conditions :
(a)
Unsymmetrical wing loads appropriate to the category. Unless the following values result in unrealistic loads, the rolling accelerations may be obtained by modifying the symmetrical .ight conditions in Sec. 23.333(d) as follows :

(1)
Forthe acrobaticcategory,in conditionsA andF, assumethat100percent of the semispan wing airload acts on one side of the plane of symmetry and 60 percent of this load acts on the other side.

(2)
[For the normal, utility, andcommuter categories,inConditionA, assume that 100percent of the semispan wing airload acts on one side of the airplane and 75 percent of this load acts on the other side.]

(b)
The loads resulting from the aileron de.ections and speeds speci.ed in Sec. 23.455, in combination with an airplane load factor of at least two thirds of the positive maneuveringloadfactor usedfordesign.Unless thefollowing values resultin unrea-listic loads, the e.ect of ailerondisplacement on wing torsion maybe accountedfor by adding the following increment to the basic airfoil moment coe.cient over the aileronportion of the spaninthe critical conditiondeterminedinSec.23.333(d) :

Δcm = .0.01δ
where– Δcm :isthe moment coe.cientincrement; and δ :is the down aileron de.ection in degrees in the critical condition. Amdt. 23-48, E.. 03/11/96
FAR 23.351 : Yawing conditions.
[The airplane must be designed for yawing loads on the vertical surfaces resulting from the loads speci.ed in Secs. 23.441 through 23.445.] Amdt. 23-42, E.. 02/04/91
　
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