14 CFR 23.725 - Limit drop tests.

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§ 23.725 Limit drop tests.
(a) If compliance with § 23.723(a) is shown by free drop tests, these tests must be made on the complete airplane, or on units consisting of wheel, tire, and shock absorber, in their proper relation, from free drop heights not less than those determined by the following formula:
h (inches)=3.6 (W/S) 1/2
However, the free drop height may not be less than 9.2 inches and need not be more than 18.7 inches.
(b) If the effect of wing lift is provided for in free drop tests, the landing gear must be dropped with an effective weight equal to
where—
W e=the effective weight to be used in the drop test (lbs.);
h=specified free drop height (inches);
d=deflection under impact of the tire (at the approved inflation pressure) plus the vertical component of the axle travel relative to the drop mass (inches);
W=W M for main gear units (lbs), equal to the static weight on that unit with the airplane in the level attitude (with the nose wheel clear in the case of nose wheel type airplanes);
W=W T for tail gear units (lbs.), equal to the static weight on the tail unit with the airplane in the tail-down attitude;
W=W N for nose wheel units lbs.), equal to the vertical component of the static reaction that would exist at the nose wheel, assuming that the mass of the airplane acts at the center of gravity and exerts a force of 1.0 g downward and 0.33 g forward; and
L= the ratio of the assumed wing lift to the airplane weight, but not more than 0.667.
(c) The limit inertia load factor must be determined in a rational or conservative manner, during the drop test, using a landing gear unit attitude, and applied drag loads, that represent the landing conditions.
(d) The value of d used in the computation of W e in paragraph (b) of this section may not exceed the value actually obtained in the drop test.
(e) The limit inertia load factor must be determined from the drop test in paragraph (b) of this section according to the following formula:
where—
n j=the load factor developed in the drop test (that is, the acceleration (dv/dt) in gs recorded in the drop test) plus 1.0; and
W e, W, and L are the same as in the drop test computation.
(f) The value of n determined in accordance with paragraph (e) may not be more than the limit inertia load factor used in the landing conditions in § 23.473.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13091, Aug. 13, 1969; Amdt. 23-48, 61 FR 5148, Feb. 9, 1996]

Title 14 published on 2015-01-01.

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  • 2015-05-21; vol. 80 # 98 - Thursday, May 21, 2015
    1. 80 FR 29205 - Special Conditions: Cirrus Design Corporation Model SF50 airplane; Full Authority Digital Engine Control (FADEC) System; Withdrawal
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions; withdrawal.
      Effective May 21, 2015, the special condition published on April 20, 2010 (75 FR 20518) is withdrawn.
      14 CFR Part 23

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United States Code

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.

  • 2015-05-21; vol. 80 # 98 - Thursday, May 21, 2015
    1. 80 FR 29205 - Special Conditions: Cirrus Design Corporation Model SF50 airplane; Full Authority Digital Engine Control (FADEC) System; Withdrawal
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions; withdrawal.
      Effective May 21, 2015, the special condition published on April 20, 2010 (75 FR 20518) is withdrawn.
      14 CFR Part 23