PORTARIA Nº 15.760, DE 31 DE OUTUBRO DE 2024 (parte 3 de 5)

(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
ANAC.
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;
(3) Provide the energy necessary to ensure each powerplant functions
properly in all likely operating conditions;
(4) provide usable energy level information to the flight crew and provide
adequate supply of that energy when the system is correctly operated, accounting for
likely energy fluctuations.
(5) Provide a means to safely remove or isolate the energy stored in the
system from the aircraft; and
(6) Be designed to retain energy under all likely operating conditions and to
minimize hazards to occupants and first responders following an emergency landing or
otherwise survivable impact (crash landing).
(b) Each energy-storage system must:
(1) Withstand the loads under likely operating conditions without failure;
and
(2) be isolated from personnel compartments and protected from likely
hazards;
(c) Each energy recharging system must be designed to:
(1) prevent improper recharging;
(2) reserved
(3) prevent the occurrence of any hazard to the aircraft or to persons during
recharging.
EVE.2435 - Reserved
EVE.2440 - Powerplant Fire Protection
There must be means to isolate and mitigate hazards to the aircraft in the
event of a powerplant-system fire or overheat in operation.
SUBPART F - EQUIPMENT EQUIPMENT
EVE.2500 - Aircraft level systems requirements.
This section applies generally to installed equipment and systems and should
not be used to supersede any other specific requirement.
(a) The equipment and systems required for an aircraft to operate safely in
the kinds of operations for which certification is requested (Day VFR, Night VFR, IFR)
must be designed and installed to:
(1) Meet the level of safety applicable to the certification and performance
level of the aircraft; and
(2) Perform their intended function throughout the operating and
environmental limits for which the aircraft is certificated.
(b) The systems and equipment not covered by paragraph (a), considered
separately and in relation to other systems, must be designed and installed so their
operation does not have an adverse effect on the aircraft or its occupants.
EVE.2505 - Function and installation.
When installed, each item of equipment must function as intended.
EVE.2510 - Equipment, systems, and installations.
This section applies generally to installed equipment and systems and should
not be used to supersede any other specific requirement. The applicant must design and
install each system and equipment, such that there is a logical and acceptable inverse
relationship between the average probability and the severity of failure conditions to the
extent that:
(a) Each catastrophic failure condition is extremely improbable and does not
result from a single failure;
(b) Each hazardous failure condition is extremely remote; and
(c) Each major failure condition is remote.
EVE.2515 - Electrical and Electronic-System Lightning Protection
(a) Each electrical or electronic system that performs a function, the failure
of which would prevent the continued safe flight and landing of the aircraft, must be
designed and installed such that:
(1) The function at the aircraft level is not adversely affected during and after
the time the aircraft is exposed to lightning; and
(2) The system recovers normal operation of that function in a timely manner
after the aircraft is exposed to lightning unless the system's recovery conflicts with other
operational or functional requirements of the system.
(b) For an aircraft approved for operation under instrument flight rules (IFR),
each electrical and electronic system that performs a function, the failure of which
would reduce the capability of the aircraft or the ability of the flight crew to respond
to an adverse operating condition, must be designed and installed such that the system
recovers normal operation of that function in a timely manner after the aircraft is
exposed to lightning.
EVE.2517 - Electrical wiring interconnection system (EWIS)
(a) EWIS means any wire, wiring device, or combination of these, including
termination devices, installed in any area of the aircraft for the purpose of transmitting
electrical energy, including data and signals between two or more intended termination
points.
(b) EWIS must be considered an integral part of the system and must be
considered in showing compliance with all applicable EVE-100 requirements.
EVE.2520 - High-intensity Radiated Fields (HIRF) protection.
(a) Each electrical and electronic systems that perform a function, the failure
of which would prevent the continued safe flight and landing of the aircraft, must be
designed and installed such that:
(1) The function at the aircraft level is not adversely affected during and after
the time the aircraft is exposed to the HIRF environment; and
(2) The system recovers normal operation of that function in a timely manner
after the aircraft is exposed to the HIRF environment, unless the system's recovery
conflicts with other operational or functional requirements of the system.
(b) Each electrical and electronic system that performs a function, the failure
of which would reduce the capability of the aircraft or the ability of the flightcrew to
respond to an adverse operating condition, must be designed and installed such that the
system recovers normal operation of that function in a timely manner after the aircraft
is exposed to the HIRF environment.
EVE.2525 - System power generation, storage, and distribution.
The power generation, storage, and distribution for any system must be
designed and installed to:
(a) Supply the power required for operation of connected loads during all
intended operating conditions;
(b) Ensure no single failure or malfunction of any one power supply,
distribution system, or other utilization system will prevent the system from supplying
the essential loads required for continued safe flight and landing; and
(c) Have enough capacity, if the primary source fails, to supply essential
loads, including noncontinuous essential loads for the time needed to complete the
function required for continued safe flight and landing.
EVE.2530 - External and cockpit lighting.
(a) The applicant must design and install all lights to minimize any adverse
effects on the performance of flightcrew duties.
(b) Any position and anti-collision lights, if required by operational rules, must
have the intensities, flash rate, colors, fields of coverage, and other characteristics to
provide sufficient time for another aircraft to avoid a collision.
(c) Any position lights, if required by operational rules, must include a red
light on the left side of the aircraft, a green light on the right side of the aircraft, spaced
laterally as far apart as practicable, and a white light facing aft, located on an aft
portion of the aircraft or on the wing tips.
(d) Any taxi and landing lights must be designed and installed so they provide
sufficient light for night operations.
EVE.2535 - Safety equipment.
Safety and survival equipment, required by the operating rules, must be
reliable, readily, easily identifiable, and clearly marked to identify its method of
operation.
EVE.2540 - Reserved
EVE.2545 - Pressurized systems elements.
Pressurized systems must withstand appropriate proof and burst pressures.
EVE.2550 - Equipment containing high-energy rotors.
Equipment containing high-energy rotors must be designed or installed to
protect the occupants and aircraft from uncontained fragments.
EVE.2555 - Installation of recorders
The aircraft must be equipped with a recorder or recorders that:
(a) is installed so as to ensure accurate and intelligible recording and
appropriate safeguarding of the data supportive for accident investigation, considering
conditions encountered during crash, water immersion or fire;
(b) is powered by the most reliable power source and remains powered for
as long as possible without jeopardizing service to essential or emergency loads and
emergency operation of the aircraft;
(c) includes features to facilitate the localization of a memory medium after
an accident;
(d) is installed so that it automatically records when the aircraft is capable of
moving under its own power; and
(e) records in an accepted format;
(f) alternatively some data may be transmitted and recorded remotely.
SUBPART G - FLIGHTCREW INTERFACE AND OTHER INFORMATION
EVE.2600 - Flightcrew interface.
(a) The pilot compartment, its equipment, and its arrangement to include
pilot view, must allow each pilot to perform their duties for all sources of lift and phases
of flight and perform any maneuvers within the operating envelope of the aircraft,
without excessive concentration, skill, alertness, or fatigue.
(b) The applicant must install flight, navigation, surveillance, and powerplant
controls and displays, as needed, so qualified flightcrew can monitor and perform
defined tasks associated with the intended functions of systems and equipment, without
excessive concentration, skill, alertness, or fatigue. The system and equipment design
must minimize flightcrew errors, which could result in additional hazards.
EVE.2605 - Installation and operation.
(a) Each item of installed equipment related to the flightcrew interface must
be labelled, if applicable, as to it identification, function, or operating limitations, or any
combination of these factors.
(b) There must be a discernible means of providing system operating
parameters required to operate the aircraft, including warnings, cautions, and normal
indications to the responsible crewmember.
(c) Information concerning an unsafe system operating condition must be
provided in a timely manner to the crewmember responsible for taking corrective action.
The information must be clear enough to avoid likely crewmember errors.
EVE.2610 - Instrument markings, control markings, and placards.
(a) Each aircraft must display in a conspicuous manner any placard and
instrument marking necessary for operation.
(b) The design must clearly indicate the function of each cockpit control,
other than primary flight controls.
(c) The applicant must include instrument marking and placard information in
the Aircraft Flight Manual.
EVE.2615 - Flight, navigation, and powerplant instruments.
(a) Installed systems must provide the flight crew member who sets or
monitors parameters for the flight, navigation, and lift/thrust system the information
necessary to do so during each phase of flight. This information must:
(1) be presented in a manner that the crew members can monitor the
parameters and trends, as needed to operate the aircraft; and
(2) include limitations, unless the limitation cannot be exceeded in all
intended operations.
(b) Indication systems that integrate the display of flight or source of
lift/thrust system parameters required to safely operate the aircraft, or required by the
operating rules, must:
(1) not inhibit the primary display of flight or source of lift/thrust system
parameters needed by any flight crew member in any normal mode of operation;
(2) In combination with other systems, be designed and installed so
information essential for continued safe flight and landing will be available to the
flightcrew in a timely manner after any single failure or probable combination of
failures.
EVE.2620 - Aircraft flight manual.