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

TEXTO OFICIAL · ÍNTEGRA

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;