14 CFR Part 23, Appendix C to Part 23 - Basic Landing Conditions

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View PDF at GPO Pt. 23, App. C
Appendix C to Part 23—Basic Landing Conditions
[C23.1 Basic landing conditions]
Condition Tail wheel type Nose wheel type
Level landing Tail-down landing Level landing with inclined reactions Level landing with nose wheel just clear of ground Tail-down landing
Note (1). K may be determined as follows: K=0.25 for W=3,000 pounds or less; K=0.33 for W=6,000 pounds 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 deflection to 100 percent deflection 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.
Note (3). Unbalanced moments must be balanced by a rational or conservative method.
Note (4). L is defined in § 23.725(b).
Note (5). n is the limit inertia load factor, at the c.g. of the airplane, selected under § 23.473 (d), (f), and (g).
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 component at c. g KnW 0 KnW KnW 0.
Lateral component in either direction at c. g 0 0 0 0 0.
Shock absorber extension (hydraulic shock absorber) Note (2) Note (2) Note (2) Note (2) Note (2).
Shock absorber deflection (rubber or spring shock absorber), percent 100 100 100 100 100.
Tire deflection Static Static Static Static Static.
Main wheel loads (both wheels) (Vr) (n-L)W (n-L)W b/d (n-L)W a′/d′ (n-L)W (n-L)W.
Main wheel loads (both wheels) (Dr) KnW 0 KnW a′/d′ KnW 0.
Tail (nose) wheel loads (Vf) 0 (n-L)W a/d (n-L)W b′/d′ 0 0.
Tail (nose) wheel loads (Df) 0 0 KnW b′/d′ 0 0.
Notes (1), (3), and (4) (4) (1) (1), (3), and (4) (3) and (4).
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13099, Aug. 13, 1969]

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  • 2015-10-30; vol. 80 # 210 - Friday, October 30, 2015
    1. 80 FR 66788 - Special Conditions: Honda Aircraft Company (Honda) Model HA-420, HondaJet; Cruise Speed Control System
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      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions.
      These special conditions are effective October 30, 2015 and are applicable on October 26, 2015.
      14 CFR Part 23

Title 14 published on 2015-01-01

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  • 2015-11-04; vol. 80 # 213 - Wednesday, November 4, 2015
    1. 80 FR 68281 - Special Conditions: Kestrel Aircraft Company, Model K-350 Turboprop, Lithium Batteries
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      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Notice of proposed special conditions.
      Send your comments on or before December 21, 2015.
      14 CFR Part 23