DOU 01/11/2024 - Diário Oficial da União - Brasil

                            Documento assinado digitalmente conforme MP nº 2.200-2 de 24/08/2001,
que institui a Infraestrutura de Chaves Públicas Brasileira - ICP-Brasil.
Este documento pode ser verificado no endereço eletrônico
http://www.in.gov.br/autenticidade.html, pelo código 05152024110100242
242
Nº 212, sexta-feira, 1 de novembro de 2024
ISSN 1677-7042
Seção 1
(e) Doors, canopies, and exits must be protected against inadvertent opening
in flight, unless shown to create no hazard when opened in flight.
EVE.2255 - Protection of Structure
(a) The applicant must protect each part of the aircraft, 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 aircraft 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.
EVE.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. If a fabrication process requires close control to
reach this objective, the applicant must perform the process under an approved process
specification.
(c) Except as provided in paragraphs (f) and (g) of this section, the applicant
must select design values that ensure material strength with probabilities that account
for the criticality of the structural element. Design values must account for the
probability of structural failure due to material variability.
(d) If material strength properties are required, a determination of those
properties must be based on sufficient tests of material meeting specifications to
establish design values on a statistical basis.
(e) If thermal effects are significant on a critical component or structure
under normal operating conditions, the applicant must determine those effects on
allowable stresses used for design.
(f) Design values, greater than the minimums specified by this section, may
be used, where only guaranteed minimum values are normally allowed, if a specimen of
each individual item is tested before use to determine that the actual strength
properties of that particular item will equal or exceed those used in the design.
(g) An applicant may use other material design values if approved by
A N AC .
EVE.2265 - Special factors of safety
(a) The applicant must determine a special factor of safety for each critical
design value for each part, article, or assembly for which that critical design value is
uncertain, and for each part, article, or assembly that is:
(1) Likely to deteriorate in service before normal replacement; or
(2) 
Subject
to 
appreciable 
variability
because 
of
uncertainties 
in
manufacturing processes or inspection methods.
(b) The applicant must determine a special factor of safety using quality
controls and specifications that account for each:
(1) Type of application;
(2) Inspection method;
(3) Structural test requirement;
(4) Sampling percentage; and
(5) Process and material control.
(c) The applicant must multiply the highest pertinent special factor of safety
in the design for each part of the structure by each limit and ultimate load, or ultimate
load only, if there is no corresponding limit load, such as occurs with emergency
condition loading.
STRUCTURAL OCCUPANT PROTECTION
EVE.2270 - Emergency conditions
(a) The aircraft, even when damaged in an emergency landing, must protect
each occupant against injury that would preclude egress when:
(1) Properly using safety equipment and features provided for in the
design;
(2) The occupant experiences ultimate static inertia loads likely to occur in an
emergency landing; and
(3) Items of mass, including engines or auxiliary power units (APUs), within or
external to the cabin, that could injure an occupant, experience ultimate static inertia
loads likely to occur in an emergency landing.
(b) The emergency landing conditions specified in paragraph (a)(1) and (a)(2)
of this section, must:
(1) Include dynamic conditions that are likely to occur in an emergency
landing; and
(2) Not generate loads experienced
by the occupants, which exceed
established human injury criteria for human tolerance due to restraint or contact with
objects in the aircraft.
(c) The aircraft must provide protection for all occupants, accounting for
likely flight, ground, and emergency landing conditions.
(d) Each occupant protection system must perform its intended function and
not create a hazard that could cause a secondary injury to an occupant. The occupant
protection system must not prevent occupant egress or interfere with the operation of
the aircraft when not in use.
(e) Each baggage and cargo compartment must:
(1) Be designed for its maximum weight of contents and for the critical load
distributions at the maximum load factors corresponding to the flight and ground load
conditions determined under these airworthiness criteria;
(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
EVE.2300 - Flight Control Systems
(a) The applicant must design flight control systems to:
(1) Operate easily, smoothly, and
positively enough to allow proper
performance of their functions;
(2) Protect against likely hazards; and
(3) Allow flight crew to be aware of the control limits.
(b) The applicant must design trim systems or trim functions, if installed, to:
(1) Protect against inadvertent, incorrect, or abrupt trim operation; and
(2) Provide information that is required for safe operation.
(c) Reserved.
EVE.2305 - Landing gear systems
(a) The landing gear must be designed to:
(1) Provide stable support and control to the aircraft during surface
operation; and
(2) Account for likely system failures and likely operation environments
(including anticipated limitation exceedances and emergency procedures).
(b) All aircraft must have a reliable means of stopping the aircraft with
sufficient kinetic energy absorption to account for landing. Aircraft that are required to
demonstrate aborted takeoff capability must account for this additional kinetic
energy.
(c) For aircraft 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.
EVE.2310 - Reserved
EVE.2311 - Bird Strike.
The aircraft must be capable of continued safe flight and landing after impact
with a 2.2-lb (1.0 kg) bird.
OCCUPANT SYSTEM DESIGN PROTECTION
EVE.2315 - Means of egress and emergency exits.
With the cabin configured for takeoff or landing, the aircraft is designed to:
(a) Facilitate rapid and safe evacuation of the aircraft in conditions likely to
occur following an emergency landing, including on water if an emergency flotation
system is included.
(b) 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 aircraft. If an emergency flotation
system is included, the means of egress must be above the water in the intended
floating attitude.
(c) Have easy access to emergency exits when present.
EVE.2320 - Occupant physical environment.
(a) The applicant must design the aircraft 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) The aircraft must provide each occupant with air at a breathable pressure,
free of hazardous concentrations of gases, vapors, and smoke during normal operations
and likely failures.
FIRE AND HIGH ENERGY PROTECTION
EVE.2325 - Fire protection.
(a) The following materials must be self extinguishing
(1) Insulation on electrical wire and electrical cable;
(2) Materials in the baggage and cargo compartments inaccessible in flight;
(b) The following materials must be flame-resistant:
(1) Materials in each compartment accessible in flight; and
(2) Any equipment associated with any electrical cable installation and that
would overheat in the event of circuit overload or fault.
(c) Thermal/acoustic materials in the fuselage, if installed, must not be a
flame propagation hazard.
(d) Sources of heat within each baggage and cargo compartment that are
capable of igniting adjacent objects must be shielded and insulated to prevent such
ignition.
(e) Each baggage and cargo compartment must -
(1) Be located where a fire would be visible to the pilots and be accessible
for the manual extinguishing of a fire,
(2) Be equipped with a smoke or fire detection system that warns the pilot, or
(3) Be constructed of, or lined with, fire resistant materials.
(f) There must be a means to extinguish any fire in the cabin such that the
pilot, while seated, can easily access the fire extinguishing means.
(g) Each area where flammable fluids or vapors might escape by leakage of
a fluid system must:
(1) Be defined; and
(2) Have a means to minimize the probability of fluid and vapor ignition, and
the resultant hazard, if ignition occurs.
(h) [Reserved]
(i) The risk of fire initiation due to anticipated heat or energy dissipation or
system failure or overheat that are expected to generate heat sufficient to ignite a fire
must be minimized.
EVE.2330 - Fire Protection in Fire Zones and Adjacent Areas
(a) Flight controls, engine mounts, and other flight structures within or
adjacent to fire zones must be capable of withstanding the effects of a fire.
(b) Engines in a fire zone must remain attached to the aircraft in the event
of a fire.
(c) In fire zones, terminals, equipment, and electrical cables used during
emergency procedures must perform their intended function in the event of a fire.
EVE.2335 - Lightning and Static Electricity Protection
(a) The aircraft must be
protected against catastrophic effects from
lightning.
(b) The aircraft must be protected against hazardous effects caused by an
accumulation of electrostatic charge.
SUBPART E - POWERPLANT
EVE.2400 - Powerplant installation.
(a) For the purpose of this subpart, the aircraft powerplant installation must
include each component necessary for propulsion, which affects propulsion safety.
(b) Each aircraft engine must have a type certificate or be approved under
the aircraft type certificate using standards found in subpart H and each propeller must
have a type certificate.
(c) The applicant must construct and arrange each powerplant installation to
account for:
(1) Likely operating conditions, including foreign-object threats;
(2) Sufficient clearance of moving parts to other aircraft parts and their
surroundings;
(3) Likely hazards in operation including hazards to ground personnel; and
(4) Vibration and fatigue.
(d) Hazardous accumulations of fluids, vapors, or gases must be isolated from
the aircraft and personnel compartments and be safely contained or discharged.
(e) Powerplant components must comply with their component limitations
and installation instructions or be shown not to create a hazard.
EVE.2405 - Power or Thrust Control System
(a) Any power or thrust control system, or powerplant control system, must
be designed so no unsafe condition results during normal operation of the system.
(b) Any single failure or likely combination of failures or malfunctions of a
power or thrust control system, or powerplant control system, must not prevent
continued safe flight and landing of the aircraft.
(c) Inadvertent flightcrew operation of a power or thrust control system, or
powerplant control system, must be prevented, or if not prevented, must not prevent
continued safe flight and landing of the aircraft.
EVE.2410 - Powerplant installation hazard assessment.
The applicant must assess each powerplant separately and in relation to
other aircraft systems and installations to show that any hazard resulting from the likely
failure of any powerplant system, component, or accessory will not:
(a) Prevent continued safe flight and landing or, if continued safe flight and
landing cannot be ensured, the hazard has been minimized;
(b) Cause serious injury that may be avoided; and
(c) Require immediate action by any crew member for continued operation of
any remaining powerplant system.
EVE.2415 - Powerplant ice protection.
(a) The aircraft design, including the induction and inlet system, must prevent
foreseeable accumulation or shedding of ice or snow that adversely affects powerplant
operation.
EVE.2420 - Reserved
EVE.2425 - Powerplant Operational Characteristics
(a) Each installed powerplant must
operate without any hazardous
characteristics during normal and emergency operation within the range of operating
limitations for the aircraft and the engine.
(b) The design must provide for the shutdown and restart of the powerplant
in flight within an established operational envelope.
EVE.2430 - Energy Systems
(a) Each energy system must:
(1) Be designed and arranged to provide independence between multiple
energy- storage and supply systems, so that failure of any one component in one system
will not result in loss of energy storage or supply of another system;
(2) Be designed to prevent catastrophic events due to lightning strikes, taking
into account direct and indirect effects on the aircraft;