# 14 CFR Part 23, Appendix D to Part 23 - Wheel Spin-Up and Spring-Back Loads

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There are 11 Updates appearing in the Federal Register for 14 CFR Part 23. View below or at eCFR (GPOAccess)
View PDF at GPO Pt. 23, App. D
Appendix D to Part 23—Wheel Spin-Up and Spring-Back Loads
(a) The following method for determining wheel spin-up loads for landing conditions is based on NACA T.N. 863. However, the drag component used for design may not be less than the drag load prescribed in § 23.479(b).
F Hmax=1/r e2I w(V HV c)nF Vmax/t S
where—
F Hmax=maximum rearward horizontal force acting on the wheel (in pounds);
r e=effective rolling radius of wheel under impact based on recommended operating tire pressure (which may be assumed to be equal to the rolling radius under a static load of n j W e) in feet;
I w=rotational mass moment of inertia of rolling assembly (in slug feet);
V H=linear velocity of airplane parallel to ground at instant of contact (assumed to be 1.2 V S 0, in feet per second);
V c=peripheral speed of tire, if prerotation is used (in feet per second) (there must be a positive means of pre-rotation before pre-rotation may be considered);
n=equals effective coefficient of friction (0.80 may be used);
F Vmax=maximum vertical force on wheel (pounds)=n j W e, where W e and n j are defined in § 23.725;
t s=time interval between ground contact and attainment of maximum vertical force on wheel (seconds). (However, if the value of F Vmax, from the above equation exceeds 0.8 F Vmax, the latter value must be used for F Hmax.)
(b) The equation assumes a linear variation of load factor with time until the peak load is reached and under this assumption, the equation determines the drag force at the time that the wheel peripheral velocity at radius r e equals the airplane velocity. Most shock absorbers do not exactly follow a linear variation of load factor with time. Therefore, rational or conservative allowances must be made to compensate for these variations. On most landing gears, the time for wheel spin-up will be less than the time required to develop maximum vertical load factor for the specified rate of descent and forward velocity. For exceptionally large wheels, a wheel peripheral velocity equal to the ground speed may not have been attained at the time of maximum vertical gear load. However, as stated above, the drag spin-up load need not exceed 0.8 of the maximum vertical loads.
(c) Dynamic spring-back of the landing gear and adjacent structure at the instant just after the wheels come up to speed may result in dynamic forward acting loads of considerable magnitude. This effect must be determined, in the level landing condition, by assuming that the wheel spin-up loads calculated by the methods of this appendix are reversed. Dynamic spring-back is likely to become critical for landing gear units having wheels of large mass or high landing speeds.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42167, Aug. 6, 1993]

Title 14 published on 2015-01-01.

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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

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 23 after this date.

• 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.