14 CFR 25.341 - Gust and turbulence loads.

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§ 25.341 Gust and turbulence loads.
(a) Discrete Gust Design Criteria. The airplane is assumed to be subjected to symmetrical vertical and lateral gusts in level flight. Limit gust loads must be determined in accordance with the provisions:
(1) Loads on each part of the structure must be determined by dynamic analysis. The analysis must take into account unsteady aerodynamic characteristics and all significant structural degrees of freedom including rigid body motions.
(2) The shape of the gust must be:
for 0 ≤ s ≤ 2H
where—
s=distance penetrated into the gust (feet);
Uds=the design gust velocity in equivalent airspeed specified in paragraph (a)(4) of this section; and
H=the gust gradient which is the distance (feet) parallel to the airplane's flight path for the gust to reach its peak velocity.
(3) A sufficient number of gust gradient distances in the range 30 feet to 350 feet must be investigated to find the critical response for each load quantity.
(4) The design gust velocity must be:
where—
Uref=the reference gust velocity in equivalent airspeed defined in paragraph (a)(5) of this section.
Fg=the flight profile alleviation factor defined in paragraph (a)(6) of this section.
(5) The following reference gust velocities apply:
(i) At the airplane design speed VC: Positive and negative gusts with reference gust velocities of 56.0 ft/sec EAS must be considered at sea level. The reference gust velocity may be reduced linearly from 56.0 ft/sec EAS at sea level to 44.0 ft/sec EAS at 15000 feet. The reference gust velocity may be further reduced linearly from 44.0 ft/sec EAS at 15000 feet to 26.0 ft/sec EAS at 50000 feet.
(ii) At the airplane design speed VD: The reference gust velocity must be 0.5 times the value obtained under § 25.341(a)(5)(i).
(6) The flight profile alleviation factor, Fg, must be increased linearly from the sea level value to a value of 1.0 at the maximum operating altitude defined in § 25.1527. At sea level, the flight profile alleviation factor is determined by the following equation:
Zmo=Maximum operating altitude defined in § 25.1527.
(7) When a stability augmentation system is included in the analysis, the effect of any significant system nonlinearities should be accounted for when deriving limit loads from limit gust conditions.
(b) Continuous Gust Design Criteria. The dynamic response of the airplane to vertical and lateral continuous turbulence must be taken into account. The continuous gust design criteria of appendix G of this part must be used to establish the dynamic response unless more rational criteria are shown.
[Doc. No. 27902, 61 FR 5221, Feb. 9, 1996; 61 FR 9533, Mar. 8, 1996]

Title 14 published on 2014-01-01

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  • 2014-11-14; vol. 79 # 220 - Friday, November 14, 2014
    1. 79 FR 68107 - Special Conditions: Dassault Model Falcon 900EX Airplane; Electronic System-Security Protection From Unauthorized External Access
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      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions, request for comments.
      Effective December 15, 2014.
      14 CFR Part 25

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United States Code

Title 14 published on 2014-01-01

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR 25 after this date.

  • 2014-11-14; vol. 79 # 220 - Friday, November 14, 2014
    1. 79 FR 68107 - Special Conditions: Dassault Model Falcon 900EX Airplane; Electronic System-Security Protection From Unauthorized External Access
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions, request for comments.
      Effective December 15, 2014.
      14 CFR Part 25