PORTARIA Nº 15.760, DE 31 DE OUTUBRO DE 2024

O SUPERINTENDENTE DE AERONAVEGABILIDADE, no uso das atribuições que lhe conferem o art. 35 do Regimento Interno, aprovado pela Resolução nº 381, de 14 de junho de 2016, e considerando o que consta do processo nº 00058.073662/2023-38, resolve:

Art. 1º Tornar público, nos termos do Anexo desta Portaria, o documento de Critérios de Aeronavegabilidade de Classe Especial para a aeronave Modelo EVE-100 da EVE SOLUÇÕES DE MOBILIDADE AÉREA URBANA LTDA.

Art. 2º Esta Portaria entra em vigor na data de sua publicação.

ROBERTO JOSÉ SILVEIRA HONORATO

ANEXO

CRITÉRIOS FINAIS DE AERONAVEGABILIDADE EVE-100

SUBPART A - GENERAL

EVE.2000 - Applicability and definitions.

(a) These airworthiness criteria prescribe airworthiness standards for the issuance of a type certificate, and changes to that type certificate, for the EVE Soluções de Mobilidade Aérea Urbana LTDA, Model EVE-100.

(b) For purposes of these airworthiness criteria, the following definitions apply:

(1) Continued safe flight and landing -

(i) for "essential performance" means the aircraft is capable of continued controlled flight and landing, possibly using emergency procedures, without requiring exceptional pilot skill, strength, or alertness

(ii) for "increased performance" means the aircraft is capable of climbing to a safe altitude, on a flightpath clear of obstacles, and maintaining level flight to a planned destination or alternate landing, possibly using emergency procedures, without requiring exceptional pilot skill, strength, or alertness.

(2) Phases of flight means ground operations, takeoff, climb, cruise, descent, approach, hover, and landing.

(3) Source of lift means one of three sources of lift: thrust‐borne, wing‐borne, and semi-‐thrust‐borne. Thrust‐borne is defined as when the weight of the aircraft is predominately supported by lift generated by engine-driven lift devices. Wing‐borne is defined as when the weight of the aircraft is predominately supported by aerodynamic lift from fixed airfoil surfaces. Semi‐thrust‐borne is the combination of thrust‐borne and wing‐borne, where both forms of lift are used to support the weight of the aircraft.

(4) Controlled emergency landing means the aircraft design allows direction and area of touchdown to be chosen while reasonably protecting occupants from serious injury, without requiring exceptional piloting skill or strength. Upon landing, some damage to the aircraft may be acceptable."

(5) Critical change of thrust means the most adverse effects on performance or handling qualities resulting from failures of the flight control or propulsive system, either singular or in combination, not shown to be extremely improbable.

(6) Local events are failures of aircraft systems and components, other than the engine control system, that may affect the installed environment of the engine or propeller control system.

(7) Approved flight envelope means the flight envelope composed of (i) the flight envelope associated to routine operational and/or prescribed conditions and (ii) the flight envelope associated to warning onset cases excluding situations associated to aircraft design limits or hard protection limits.

EVE.2005 - Reserved.

EVE.2010 - Accepted means of compliance.

(a) An applicant must comply with this regulation using a means of compliance, which may include consensus standards, accepted by the ANAC.

(b) An applicant requesting acceptance of a means of compliance must provide the means of compliance to ANAC in a form and manner acceptable to ANAC.

SUBPART B - FLIGHT PERFORMANCE

EVE.2100 - Weight and center of gravity

(a) The applicant must determine limits for weights and centers of gravity that provide for the safe operation of the aircraft.

(b) The applicant must comply with each requirement at critical combinations of weight and center of gravity within the aircraft's range of loading conditions using tolerances acceptable to ANAC.

(c) The condition of the aircraft at the time of determining its empty weight and center of gravity must be well defined and easily repeatable.

EVE.2105 - Performance data

(a) Unless otherwise prescribed, the aircraft must meet the performance requirements of this subpart in still air and standard atmospheric conditions.

(b) Unless otherwise prescribed, the applicant must develop the performance data required for the following conditions:

(1) Altitudes from the minimum to the maximum altitude for which certification is being sought; and

(2) Temperatures above and below standard day temperature that are within the range of operating limitations, if those temperatures could have a negative effect on performance.

(c) The procedures used for determining takeoff and landing performance must be executable consistently by pilots of average skill in atmospheric conditions expected to be encountered in service.

(d) Performance data determined in accordance with paragraph (b) of this section must account for losses due to atmospheric conditions, cooling needs, installation losses, downwash considerations, and other demands on power sources.

(e) The hovering ceiling, in and out of ground effect, must be determined over the ranges of weight, altitude, and temperature, if applicable.

(f) Continued safe flight and landing must be possible from any point within the approved flight envelope following a critical change of thrust.

(g) Following a condition when the aircraft can no longer provide the commanded power or thrust for continued safe flight and landing, the aircraft must be capable of a controlled emergency landing without requiring exceptional pilot skill, strength, or alertness.

EVE.2110 - Minimum safe speed.

The applicant must determine the aircraft minimum safe speed for each flight condition encountered in normal operations, including applicable source(s) of lift and phase(s) of flight, to maintain controlled safe flight. The minimum safe speed determination must account for the most adverse conditions for each flight configuration.

EVE.2115 - Takeoff performance.

(a) The applicant must determine takeoff performance accounting for:

(1) All sources of lift for each takeoff flight path for which certification is sought;

(2) Minimum safe speed safety margins;

(3) Climb requirements; and

(4) Obstacle Clearance.

(b) For aircraft approved for essential performance, the applicant must determine the takeoff performance to a safe height above the takeoff. Additionally, the aircraft must perform a continued safe flight and landing according to EVE.2105(f) at any point along the takeoff flight path.

(c) For aircraft approved for increased performance, the takeoff performance must be determined so that, following a critical change of thrust:

(1) Prior to reaching the takeoff decision point:

(i) A rejected takeoff resulting in a safe stop and landing can be made. The takeoff decision point may be a speed, an altitude, or both; and

(2) After passing the takeoff decision point:

(i) Continue the takeoff and climb to a safe height above the takeoff surface;

(ii) The aircraft can achieve the configuration and airspeed used in compliance with EVE 2120(d)(1); and

(iii) The aircraft must perform a continued safe flight and landing according to EVE.2105(f).

EVE.2120 - Climb requirements

(a) The applicant must demonstrate minimum climb performance out of ground effect at each weight, altitude, and ambient temperature within the operating limitations using the procedures published in the flight manual.

(b) For aircraft approved for essential and increased performance, the applicant must determine the following all engines operating (AEO) climb performance requirements:

(1) The aircraft must have a minimum steady climb gradient at sea level in the initial takeoff configuration(s) and a climb speed selected by the applicant or Vy, and

(2) For a balked landing, the aircraft must be able to maintain a minimum steady climb gradient without creating undue pilot workload in the landing configuration(s).

(c) For aircraft approved for essential performance, the climb performance after a critical change of thrust must be determined:

(1) Using applicable sources of lift along the takeoff flight path for which certification is being sought at the speeds and configurations selected by the applicant; and

(2) For the transition from the takeoff to the enroute configuration. The total altitude loss must be determined for the weight, altitude, and ambient temperature where level flight cannot be maintained.

(d) For aircraft approved for increased performance, the climb performance after a critical change of thrust must be such that during climb:

(1) Takeoff phase or following a balked landing:

(i) The trajectory must clear all obstacles by sufficient margins for takeoff or landing and reach the Takeoff Safety Speed (VTOSS) at a safe height above the takeoff or landing surface with a positive rate of climb;

(ii) The minimum rate of climb at initial takeoff height above the takeoff or landing surface in VTOSS is assured;

(iii) The minimum rate of climb at final takeoff height above the takeoff or landing surface in Final Takeoff Speed (VFTO) is assured;

(iv) From the initial takeoff height above the takeoff or landing surface, the aircraft path must be level or positive until the VFTO or the final takeoff height is attained, whichever is higher, with available rate of climb not less than the required by (d)(1)(iii).

(2) Enroute:

(i) Where applicable, the steady rate of climb (or descent) must be determined at each weight, altitude, temperature and sources of lift at which the aircraft is expected to operate for which certification is requested.

EVE.2125 - Climb information

(a) The applicant must determine climb performance at each weight, altitude, and ambient temperature within the operating limitations using the procedures published in the flight manual.

(b) The applicant must determine climb performance accounting after a critical change of thrust.

(c) The applicant must determine the performance accordingly for the appropriate sources of lift applicable to the condition defined in EVE.2105(g).

EVE.2130 - Landing.

The applicant must determine the following, for the critical combinations of weight, altitudes and temperatures within the operational limits:

(a) The approach, transition and landing speeds and procedures, which allow a pilot of average skill to land within the published landing performance consistently and without causing damage or injury, and which allow for a safe transition to the balked landing conditions of these airworthiness criteria accounting for:

(1) All sources of lift for each approach and landing flight path for which certification is sought; and

(2) Any minimum or maximum speed safety margins.

(b) For aircraft approved for essential performance, the applicant must determine the landing performance from a safe height above the landing surface. Additionally, the aircraft must perform a continued safe flight and landing according to EVE.2105(f) at any point along the approach flight path.

(c) For aircraft approved for increased performance, the applicant must determine the landing performance from a safe height above the landing surface so that, following a critical change of thrust that occurs:

(1) Prior to reaching the landing decision point, the aircraft can-

(i) Land and stop safely on the landing surface; or

(ii) Transition to the balked landing condition established in EVE.2120(d)(1) and perform a continued safe flight and landing according to EVE.2105(f).

(2) After passing the landing decision point, the aircraft can-

(i) Land and stop safely on the landing surface.

FLIGHT CHARACTERISTICS

EVE.2135 - Controllability

(a) The aircraft must be controllable and maneuverable, without requiring exceptional piloting skill, alertness, or strength, within the approved flight envelope:

(1) At all loading conditions for which certification is requested;

(2) During all phases of flight while using applicable sources of lift;

(3) With flight control or propulsion systems failures, in a complementary approach to the airworthiness criteria EVE.2510 for handling qualities aspects evaluation;

(4) During configuration changes;

(5) In all degraded flight control and propulsion systems operating modes not shown to be extremely improbable;

(6) In thrust-borne operation, and must be controllable in wind velocities from zero to at least 17 knots from any azimuth angle; and

(7) The aircraft must be able to safely complete a landing using the steepest approach gradient procedures.

(b) The applicant must determine critical control parameters, such as limited control power margins, and if applicable, account for those parameters in appropriate operating limitations.

(c) It must be possible to make a smooth transition from one flight condition to another (changes in configuration and in source of lift and phase of flight) without exceeding the approved flight envelope.

(d) Operation of features that protect the aircraft against loss of control, or exceeding critical limits, must not adversely affect flight characteristics in aircraft response to inceptor inputs, unsteady atmospheric conditions, and other likely conditions, including simultaneous limiting events.

EVE.2140 - Trim

(a) The aircraft must maintain lateral and directional trim without further force upon, or movement of, the inceptor by the pilot, under all normal operations while using applicable sources of lift.

(b) The aircraft must maintain longitudinal trim without further force upon, or movement of, the inceptor by the pilot, under the following conditions:

(1) Climb.

(2) Level flight.

(3) Descent.

(4) Approach.

(c) Residual control forces must not fatigue or distract the pilot during normal operations of the aircraft and abnormal or emergency operations, including a critical change of thrust.

EVE.2145 - Stability

(a) Within the approved flight envelope, the aircraft must show suitable stability and control feel, in all axes.

(b) Within the approved flight envelope, no aircraft may exhibit any divergent stability characteristic, so as to require exceptional piloting skills, alertness, or strength or otherwise endanger the aircraft and its occupants.

EVE.2150 - Minimum safe speed characteristics and warning.

(a) For wing borne operation, the aircraft must have controllable minimum safe speed flight characteristics in straight flight, turning flight, and accelerated turning flight. In case there is no high incidence protection system, there must be a clear and distinctive minimum safe speed warning that provides sufficient margin to prevent inadvertently slowing below the minimum safe speed.

(b) For wing borne and semi-thrust-borne operations, the aircraft must not have a tendency to inadvertently depart controlled safe flight, including a sudden change of thrust.

EVE.2155 - Ground handling characteristics.

For aircraft intended for operation on land or water, the aircraft must have controllable longitudinal and directional handling characteristics during taxi, takeoff, and landing operations.

EVE.2160 - Vibration, buffeting, and high-speed characteristics

(a) Each part of the aircraft must be free from excessive vibration and buffeting under each appropriate speed and power condition. Vibration and buffeting, for operations up to VD /MD, must not interfere with the control of the aircraft or cause excessive fatigue to the flightcrew. Stall warning buffet within these limits is allowable.

(b) For inadvertent excursions beyond the maximum approved speed, the aircraft must be able to safely recover back to its approved flight envelope without requiring exceptional piloting skill, strength, or alertness. This recovery may not result in structural damage or loss of control.

EVE.2165 - Performance and flight characteristics requirements for flight in atmospheric icing conditions.

(a) Reserved

(b) The applicant must provide a means to detect icing conditions for which certification is not requested and show the aircraft's ability to avoid or exit those icing conditions.

(c) The applicant must develop an operating limitation to prohibit intentional flight, including takeoff and landing, into icing conditions for which the aircraft is not certified to operate.

SUBPART C - STRUCTURES

EVE.2200 - Structural design envelope

The applicant must determine the structural design envelope, which describes the range and limits of aircraft design and operational parameters for which the applicant will show compliance with the requirements of this subpart. The applicant must account for all aircraft design and operational parameters that affect structural loads, strength, durability, and aeroelasticity, including:

(a) Structural design airspeeds, landing descent speeds, and any other airspeed limitation at which the applicant must show compliance to the requirements of this subpart. The structural design airspeeds must:

(1) Be sufficiently greater than the minimum safe speed of the aircraft to safeguard against loss of control in turbulent air; and

(2) Provide sufficient margin for the establishment of practical operational limiting airspeeds.

(b) Design maneuvering load factors not less than those, which service history shows, may occur within the structural design envelope.

(c) Inertial properties including weight, center of gravity, and mass moments of inertia, accounting for:

(1) Each critical weight from the aircraft empty weight to the maximum weight; and

(2) The weight and distribution of occupants, payload, and energy-storage systems.

(d) Characteristics of aircraft 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.

(f) Engine-driven lifting/thrusting-device rotational speed and ranges, and the maximum rearward and sideward flight speeds.

(g) Thrust‐borne, wing‐borne, and semi‐thrust‐borne flight configurations, with associated flight load envelopes.

EVE.2205 - Interaction of systems and structures

For aircraft 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

EVE.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 aircraft 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.

EVE.2215 - Flight Load Conditions

(a) The applicant must determine the structural design loads resulting from the following flight conditions:

(1) Atmospheric gusts where the magnitude and gradient of these gusts are based on measured gust statistics.

(2) Symmetric and asymmetric maneuvers.

(3) Asymmetric thrust resulting from the failure of a powerplant unit.

(b) There must be no vibration or buffeting severe enough to result in structural damage, at any speed up to dive speed, within the structural design envelope, in any configuration and power settings.

EVE.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.

EVE.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) Reserved.

(d) Engine-driven lifting/thrusting-device assemblies, considering loads resulting from flight and ground conditions, as well limit input torque at any lifting/thrusting- device rotational speed.

EVE.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 these airworthiness criteria; 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 these airworthiness criteria.

STRUCTURAL PERFORMANCE

EVE.2235 - Structural strength

The structure must support:

(a) limit loads without:

(1) interference with the safe operation of the aircraft; and

(2) detrimental or permanent deformation.

(b) ultimate loads.

EVE.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 EVE.1529.

(b) If safety-by-design (fail-safe) is used to comply with paragraph (a) of this section, safety-by-inspection (damage tolerance) must also be incorporated to reliably detect structural damage before the damage could result in structural failure.

(c) Reserved.

(d) The aircraft must be designed to minimize hazards to the aircraft due to structural damage caused by high-energy fragments from an uncontained engine or rotating machinery failure.

EVE.2241 - Aeromechanical stability

The aircraft must be free from dangerous oscillations and aeromechanical instabilities for all configurations and conditions of operation on the ground and in flight.

EVE.2245 - Aeroelasticity

(a) The aircraft 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 structural modes; and

(4) Accounting for any critical failures or malfunctions.

(b) The applicant must establish tolerances for all quantities that affect aeroelastic stability.

(c) Each component and rotating aerodynamic surface of the aircraft must be free from any aeroelastic instability under each appropriate speed and power condition.

DESIGN

EVE.2250 - Design and construction principles

(a) The applicant must design each part, article, and assembly for the expected operating conditions of the aircraft.

(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. The applicant must prevent single failures from resulting in a catastrophic effect upon the aircraft.

(d) The control system must be free from jamming, excessive friction, and excessive deflection when the aircraft 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.

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 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.

The applicant must provide an Aircraft Flight Manual that must be delivered with each aircraft.

(a) The Aircraft Flight Manual must contain the following information:

(1) Aircraft operating limitations;

(2) Aircraft operating procedures;

(3) Performance information;

(4) Loading information; and

(5) Other information that is necessary for safe operation because of design, operating, or handling characteristics.

(b) The portions of the Aircraft Flight Manual containing the information specified in paragraphs (a)(1) through (a)(4) of this section must be approved by the ANAC.