Federal Aviation Administration, DOT

Section 23.2320

(2) Have a means to prevent the contents of the compartment from becoming a hazard by impacting occupants or
shifting; and
(3) Protect any controls, wiring,
lines, equipment, or accessories whose
damage or failure would affect safe operations.

Subpart D - Design and
Construction

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Section 23.2300 Flight control systems.
(a) The applicant must design airplane flight control systems to:
(1) Operate easily, smoothly, and
positively enough to allow proper performance of their functions.
(2) Protect against likely hazards.
(b) The applicant must design trim
systems, if installed, to:
(1) Protect against inadvertent, incorrect, or abrupt trim operation.
(2) Provide a means to indicate - 
(i) The direction of trim control
movement relative to airplane motion;
(ii) The trim position with respect to
the trim range;
(iii) The neutral position for lateral
and directional trim; and
(iv) The range for takeoff for all applicant requested center of gravity
ranges and configurations.
Section 23.2305 Landing gear systems.
(a) The landing gear must be designed to - 
(1) Provide stable support and control
to the airplane during surface operation; and
(2) Account for likely system failures
and likely operation environments (including
anticipated
limitation
exceedances and emergency procedures).
(b) All airplanes must have a reliable
means of stopping the airplane with
sufficient kinetic energy absorption to
account for landing. Airplanes that are
required to demonstrate aborted takeoff capability must account for this additional kinetic energy.
(c) For airplanes that have a system
that actuates the landing gear, there
is - 
(1) A positive means to keep the landing gear in the landing position; and
(2) An alternative means available to
bring the landing gear in the landing

position when a non-deployed system
position would be a hazard.
Section 23.2310 Buoyancy for seaplanes and
amphibians.
Airplanes intended for operations on
water, must - 
(a) Provide buoyancy of 80 percent in
excess of the buoyancy required to support the maximum weight of the airplane in fresh water; and
(b) Have sufficient margin so the airplane will stay afloat at rest in calm
water without capsizing in case of a
likely float or hull flooding.
OCCUPANT SYSTEM DESIGN PROTECTION
Section 23.2315 Means of egress and emergency exits.
(a) With the cabin configured for
takeoff or landing, the airplane is designed to:
(1) Facilitate rapid and safe evacuation of the airplane in conditions likely to occur following an emergency
landing, excluding ditching for level 1,
level 2 and single engine level 3 airplanes.
(2) Have means of egress (openings,
exits or emergency exits), that can be
readily located and opened from the inside and outside. The means of opening
must be simple and obvious and
marked inside and outside the airplane.
(3) Have easy access to emergency
exits when present.
(b) Airplanes approved for aerobatics
must have a means to egress the airplane in flight.
Section 23.2320 Occupant physical environment.
(a) The applicant must design the
airplane to - 
(1) Allow clear communication between the flightcrew and passengers;
(2) Protect the pilot and flight controls from propellers; and
(3) Protect the occupants from serious injury due to damage to windshields, windows, and canopies.
(b) For level 4 airplanes, each windshield and its supporting structure directly in front of the pilot must withstand, without penetration, the impact
equivalent to a two-pound bird when
the velocity of the airplane is equal to
the airplane-s maximum approach flap
speed.

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