11IL-S-6252D
3.2.13.1 Vibration. (Sample statement): The design of the airplane shall be such that the probability of disastrous fatigue failure resulting from vibrations (including those produced by noise or other oscillatory air flows) during the service life (insert flight hours of life) of the airplane will not ex- ceed . In those types of structure where redundancy, slow rate of crack growth and inspection enable repair in time to avoid disastrous fatigue failure or reduction in strength, the design of the airplane shall be such that the repair rate (Le., total man- hours of repair time divided by the life of the .airplane in flight hours) in normal serv- ice operation does not exceed ----
3.2.13.2 Crew comfort.
3.2.13.2.1 Acoustical noise. (Sample state- ment) : Acoustical noise shall not exceed the limits stated in Specification MIL-A-8806 and shall be measured as required therein.
3.2.13.2.2 Vibration. (Sample statement) : The vibration of crew seats, rudder pedals, heel troughs, control columns, work tables, .
primary structural members· in au .oc- cupied areas during unaccelerated flight from minimum to maximum cruising speed shall not exceed acceleration at fre- q1;tencies below cps, inches
double amplitude at frequencies between
--- cps and cps.
3.2.14 A i r cr a f t sustailLed operation. (Sample statement): The aircraft shall be capable of performing missions within the performance envelope on a sustained basis. That is, the aircraft is expected to be avail- able for operational missions approximately
--- percent of the time.
3.3 Aerodynamics. ('l'he detailed require- ments pertaining to aerodynamic charac- teristics of the aircraft shall be included as subparagraphs of this paragraph.)
3.3.1 General. (Give general overall char-
acteristics in this paragraph. The designer shall use this section to describe or specify any aerodynamic features or devices not de- scribed in detail elsewhere in this specifica- tion. Examples are: Smoothness of exterior joints, fairness of surfaces and trueness of contours, cleanness of intersections, sealing against air leakage which may cause drag, and similar items.)
3.3.2 Stability and cfnitrol.
3.3.2.1 (Sample statement): Stability 'and control characteristics shall be in accordance with the requirements of Specification MIL- F-8785.
3.3.2.2 Center of gravity li'mits. (See
3.1.4) (The designer may insert any addi- tional information pertinent to center of gravity travel and its effect on stability and control.)
3.a.3 (USAF) Flutter characteristics. (Sample statement): The aircraft and all its components shall be fr,ee from divergence, flutter, buzz, or other aeroelastic instability throughout the entire range of permissible speeds, altitudes, maneuvers, aerodynamic and acceleration loading conditions, and weight conditions as determined by methods and criteria in Specification MIL-F-25352.
3.4 (USAF) Structural design criteria. (Sample statement): Structural design of this· aircraft is in conformance with the cri- teria specified in Specification MIL-S-5700. Structural parameters are listed herein.
3.4.1 Li.mit flight load factors. (Note: The
•information to be supplied below · shall be
based en certain typieal loading conditions specified in the design requirements docu- ments or the applicable strength specifica- tion. Any information at variance with the des i g n requireinents document 01· the strength specification shall be covered by acceptable deviations and listed in appendix II. The design weightsIisted in the following
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