JAR 25.321 General
(a) Flight load factors represent the ratio of
the aerodynamic force component (acting normal
to the assumed longitudinal axis of the aeroplane)
to the weight of the aeroplane. A positive load
factor is one in which the aerodynamic force acts
upward with respect to the aeroplane.
(b) Considering compressibility effects at
each speed, compliance with the flight load
requirements of this Subpart must be shown –
(1) At each critical altitude within the
range of altitudes selected by the applicant;
(2) At each weight from the design
minimum weight to the design maximum
weight appropriate to each particular flight
load condition; and
(3) For each required altitude and
weight, for any practicable distribution of
disposable load within the operating limitations
recorded in the Aeroplane Flight Manual.
[(c) Enough points on and within the
boundaries of the design envelope must be
investigated to ensure that the maximum load for
each part of the aeroplane structure is obtained.
(d) The significant forces acting on the
aeroplane must be placed in equilibrium in a
rational or conservative manner. The linear
inertia forces must be considered in equilibrium
with the thrust and all aerodynamic loads, while
the angular (pitching) inertia forces must be
considered in equilibrium with thrust and all
aerodynamic moments, including moments due to
loads on components such as tail surfaces and
nacelles. Critical thrust values in the range from
zero to maximum continuous thrust must be
considered.]
|