183
Federal Aviation Administration, DOT
§ 23.2225
(b) Design maneuvering load factors
not less than those, which service his-
tory shows, may occur within the
structural design envelope.
(c) Inertial properties including
weight, center of gravity, and mass
moments of inertia, accounting for—
(1) Each critical weight from the air-
plane empty weight to the maximum
weight; and
(2) The weight and distribution of oc-
cupants, payload, and fuel.
(d) Characteristics of airplane con-
trol systems, including range of motion
and tolerances for control surfaces,
high-lift devices, or other moveable
surfaces.
(e) Each critical altitude up to the
maximum altitude.
[Doc. No. FAA–2015–1621, Amdt. 23–64, 81 FR
96689, Dec. 30, 2016, as amended by Doc. No.
FAA–2022–1355, Amdt. 23–65, 87 FR 75710, Dec.
9, 2022]
§ 23.2205
Interaction of systems and
structures.
For airplanes equipped with systems
that modify structural performance,
alleviate the impact of this subpart’s
requirements, or provide a means of
compliance with this subpart, the ap-
plicant must account for the influence
and failure of these systems when
showing compliance with the require-
ments of this subpart.
S
TRUCTURAL
L
OADS
§ 23.2210
Structural design loads.
(a) The applicant must:
(1) Determine the applicable struc-
tural design loads resulting from likely
externally or internally applied pres-
sures, forces, or moments that may
occur in flight, ground and water oper-
ations, ground and water handling, and
while the airplane is parked or moored.
(2) Determine the loads required by
paragraph (a)(1) of this section at all
critical combinations of parameters,
on and within the boundaries of the
structural design envelope.
(b) The magnitude and distribution of
the applicable structural design loads
required by this section must be based
on physical principles.
§ 23.2215
Flight load conditions.
The applicant must determine the
structural design loads resulting from
the following flight conditions:
(a) Atmospheric gusts where the
magnitude and gradient of these gusts
are based on measured gust statistics.
(b) Symmetric and asymmetric ma-
neuvers.
(c) Asymmetric thrust resulting from
the failure of a powerplant unit.
§ 23.2220
Ground and water load con-
ditions.
The applicant must determine the
structural design loads resulting from
taxi, takeoff, landing, and handling
conditions on the applicable surface in
normal and adverse attitudes and con-
figurations.
§ 23.2225
Component loading condi-
tions.
The applicant must determine the
structural design loads acting on:
(a) Each engine mount and its sup-
porting structure such that both are
designed to withstand loads resulting
from—
(1) Powerplant operation combined
with flight gust and maneuver loads;
and
(2) For non-reciprocating power-
plants, sudden powerplant stoppage.
(b) Each flight control and high-lift
surface, their associated system and
supporting structure resulting from—
(1) The inertia of each surface and
mass balance attachment;
(2) Flight gusts and maneuvers;
(3) Pilot or automated system inputs;
(4) System induced conditions, in-
cluding jamming and friction; and
(5) Taxi, takeoff, and landing oper-
ations on the applicable surface, in-
cluding downwind taxi and gusts occur-
ring on the applicable surface.
(c) A pressurized cabin resulting from
the pressurization differential—
(1) From zero up to the maximum re-
lief pressure combined with gust and
maneuver loads;
(2) From zero up to the maximum re-
lief pressure combined with ground and
water loads if the airplane may land
with the cabin pressurized; and
(3) At the maximum relief pressure
multiplied by 1.33, omitting all other
loads.
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