WW
1. Conditions “C”.or “F”.need only be investigated when n3 or n4 is
SS
WW
greater than n1 or n2 , respectively.
SS
2. Condition “G”.need not be investigated when the supplementary condition specified in FAR 23.369 is investigated.
Fig. 35.6 – Flight envelope.
′
Elodie Roux. Septembre 2003
Appendix A : Simpli.ed Design Load Criteria
Average surface loading
pounds/sq.ft
Design maneuvering wing loading n1W/S pounds/sq.ft
Design maneuvering wing loading n1W/S pounds/sq.ft
leading. Trailing. edge edge
Fig. 35.9 – [Chordwise load distribution for stabilizer andelevator or .n and rudder.]
[
2.E .3d.
P1 =2ˉw
1.E P2 =2ˉw (3d. + E .1)
where —
wˉaveragesurfaceloading(asspeci.edin (Figure 35.7, p. 454)) E Ratio of elevator(or rudder) chord to total stabilizer and elevator(or .n and rudder) chord
d. Ratio of distance of center of pressure of unit spanwise length of combined stabilizer and elevator(or .n and rud-der) measuredfromstabilizer(or .n) leading edgetothe local chord.Sign conventionispositive when center ofpres-sure is behind leading edge.
c Local chord
NOTE : Positive values of ˉw, P1 and P2 are all measuredinthe samedirection.][Amdt. 23-48, E.. 03/11/96]
′
Elodie Roux. Septembre 2003
Appendix A : Simpli.ed Design Load Criteria
Chapitre 36
Appendix B : Control Surface Loadings
Sommaire
FAR23.B1:[Reserved.] ..................... 458
FAR23.B11:[Reserved.] .................... 458
457
Appendix B : Control Surface Loadings
FAR23.B1 :[Reserved.]
[Reserved.] Amdt. 23-42, E.. 02/04/91
FAR23.B11 :[Reserved.]
[Reserved.] Amdt. 23-42, E.. 02/04/91
Chapitre 37
Appendix C : Basic Landing Conditions
Sommaire
FAR23.C.1:Basiclanding conditions. . . . . . . . . . . . . . 460
459
Appendix C : Basic Landing Conditions
FAR 23.C.1 : Basic landing conditions.
Condition Tail wheel type Nose wheel type
Level landing Tail-down landing Level lan-ding with inclined reactions Level lan-ding with nose wheel just clear of ground Tail-down landing
Reference section 23.479(a)(1) 23.481(a)(1) 23.479(a)(2)(i) 23.479(a)(2)(ii) 23.481(a)(2) and (b)
Vertical component at c.g. nW nW nW nW nW
Fore and aft com-ponent at c.g. KnW 0 KnW KnW 0
Lateral component in either direction at c.g. 0 0 0 0 0
Shock absorber exten-sion (hydraulic shock absorber) Note (2) Note (2) Note (2) Note (2) Note (2)
Shock absorber de.ec-tion (rubber or spring shock absorber) 100% 100% 100% 100% 100%
Tire de.ection Static Static Static Static Static
KnW 0 KnWa’/d’ KnW 0
0 0 KnWb’/d’ 0 0
Notes (1), (3), and (4) (4) (1) (1), (3), and (4) (3)and (4)
Note(1) . K may be determined as follows : K =0.25 for W =3,000pounds or less; K =0.33 for W =6,000pounds or greater, with linear variation of K between these weights.
Note(2) . For the purpose of design, the maximum load factor is assumed to occur throughout the shock absorber stroke from 25 percent de.ection to 100 percent de.ection unless otherwise shown and the load factor must be used with whatever shock absorber extension is most critical for each element of the landing gear.
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