Limit drop tests.
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.
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
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.
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.
The limit inertia load factor must be determined from the drop test in paragraph (b) of this section according to the following formula:
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]