Section 23.2205

14 CFR Ch. I (1-1-19 Edition)

(2) The weight and distribution of occupants, payload, and fuel.
(d) Characteristics of airplane control 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.
Section 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 applicant must account for the influence
and failure of these systems when
showing compliance with the requirements of this subpart.
STRUCTURAL LOADS
Section 23.2210 Structural design loads.
(a) The applicant must:
(1) Determine the applicable structural design loads resulting from likely
externally or internally applied pressures, forces, or moments that may
occur in flight, ground and water operations, 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.

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Section 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 maneuvers.
(c) Asymmetric thrust resulting from
the failure of a powerplant unit.
Section 23.2220 Ground and water load conditions.
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 configurations.
Section 23.2225 Component loading conditions.
The applicant must determine the
structural design loads acting on:
(a) Each engine mount and its supporting 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 powerplants, 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, including jamming and friction; and
(5) Taxi, takeoff, and landing operations on the applicable surface, including downwind taxi and gusts occurring on the applicable surface.
(c) A pressurized cabin resulting from
the pressurization differential - 
(1) From zero up to the maximum relief pressure combined with gust and
maneuver loads;
(2) From zero up to the maximum relief 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.
Section 23.2230 Limit and ultimate loads.
The applicant must determine - 
(a) The limit loads, which are equal
to the structural design loads unless
otherwise specified elsewhere in this
part; and
(b) The ultimate loads, which are
equal to the limit loads multiplied by a
1.5 factor of safety unless otherwise
specified elsewhere in this part.
STRUCTURAL PERFORMANCE
Section 23.2235 Structural strength.
The structure must support:

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