Federal Aviation Administration, DOT

Section 23.2260

(a) Limit loads without - 
(1) Interference with the safe operation of the airplane; and
(2) Detrimental permanent deformation.
(b) Ultimate loads.

(4) Accounting for any critical failures or malfunctions.
(b) The applicant must establish tolerances for all quantities that affect
flutter.
DESIGN

spaschal on DSK3GDR082PROD with CFR

Section 23.2240 Structural durability.
(a) The applicant must develop and
implement inspections or other procedures to prevent structural failures due
to foreseeable causes of strength degradation, which could result in serious
or fatal injuries, or extended periods of
operation with reduced safety margins.
Each of the inspections or other procedures developed under this section
must be included in the Airworthiness
Limitations Section of the Instructions
for Continued Airworthiness required
by Section 23.1529.
(b) For Level 4 airplanes, the procedures developed for compliance with
paragraph (a) of this section must be
capable of detecting structural damage
before the damage could result in
structural failure.
(c) For pressurized airplanes:
(1) The airplane must be capable of
continued safe flight and landing following a sudden release of cabin pressure, including sudden releases caused
by door and window failures.
(2) For airplanes with maximum operating altitude greater than 41,000
feet, the procedures developed for compliance with paragraph (a) of this section must be capable of detecting damage to the pressurized cabin structure
before the damage could result in rapid
decompression that would result in serious or fatal injuries.
(d) The airplane must be designed to
minimize hazards to the airplane due
to structural damage caused by highenergy fragments from an uncontained
engine or rotating machinery failure.
Section 23.2245 Aeroelasticity.
(a) The airplane must be free from
flutter, control reversal, and divergence - 
(1) At all speeds within and sufficiently beyond the structural design
envelope;
(2) For any configuration and condition of operation;
(3) Accounting for critical degrees of
freedom; and

Section 23.2250 Design
and
construction
principles.
(a) The applicant must design each
part, article, and assembly for the expected operating conditions of the airplane.
(b) Design data must adequately define the part, article, or assembly configuration, its design features, and any
materials and processes used.
(c) The applicant must determine the
suitability of each design detail and
part having an important bearing on
safety in operations.
(d) The control system must be free
from jamming, excessive friction, and
excessive deflection when the airplane
is subjected to expected limit airloads.
(e) Doors, canopies, and exits must be
protected against inadvertent opening
in flight, unless shown to create no
hazard when opened in flight.
Section 23.2255 Protection of structure.
(a) The applicant must protect each
part of the airplane, including small
parts such as fasteners, against deterioration or loss of strength due to any
cause likely to occur in the expected
operational environment.
(b) Each part of the airplane must
have adequate provisions for ventilation and drainage.
(c) For each part that requires maintenance, preventive maintenance, or
servicing, the applicant must incorporate a means into the aircraft design
to allow such actions to be accomplished.
Section 23.2260 Materials and processes.
(a) The applicant must determine the
suitability and durability of materials
used for parts, articles, and assemblies,
accounting for the effects of likely environmental conditions expected in
service, the failure of which could prevent continued safe flight and landing.
(b) The methods and processes of fabrication and assembly used must
produce consistently sound structures.

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