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 05152024110100243 243 Nº 212, sexta-feira, 1 de novembro de 2024 ISSN 1677-7042 Seção 1 (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 A N AC . SUBPART H - ELECTRIC ENGINE REQUIREMENTS EVE.3305 - Instruction manual for installing and operating the engine. (a) Installation instructions. (1) The location of engine mounting attachments, the method of attaching the engine to the aircraft, and the maximum allowable load for the mounting attachments and related structure. (2) The location and description of engine connections to be attached to accessories, pipes, wires, cables, ducts, and cowling. (3) An outline drawing of the engine including overall dimensions. (4) A definition of the physical and functional interfaces with the aircraft and aircraft equipment, including the propeller when applicable. (5) Where an engine system relies on components that are not part of the engine type design, the interface conditions and reliability requirements for those components upon which engine type certification is based must be specified in the engine installation instructions directly or by reference to appropriate documentation. (6) A list of the instruments necessary for control of the engine, including the overall limits of accuracy and transient response required of such instruments for control of the operation of the engine, must also be stated so that the suitability of the instruments as installed may be assessed. (b) Operation instructions. (1) The operating limitations established by ANAC. (2) The power or thrust ratings and procedures for correcting for nonstandard atmosphere. (3) The recommended procedures, under normal and extreme ambient conditions for: (i) Starting; (ii) Operating on the ground; and (iii) Operating during flight. (4) For engines having one or more engine inoperative ratings or other contingency ratings, applicants must provide data on engine performance characteristics and variability to enable the aircraft manufacturer to establish aircraft power assurance procedures. (5) A description of the primary and all alternate modes, and any back-up system, together with any associated limitations, of the engine control system and its interface with the aircraft systems, including the propeller when applicable.