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

EVE.3389 - Operation demonstration
The engine design must demonstrate safe operating characteristics, including
but not limited to power cycling, starting, acceleration, and overspeeding throughout its
declared flight envelope and operating range. The declared engine operational
characteristics must account for installation loads and effects.
EVE.3390 - Durability Demonstration
The engine must be subjected to a durability demonstration to show that each
part of the engine has been designed and constructed to minimize any unsafe condition of
the system between overhaul periods or between engine replacement intervals if the
overhaul is not defined. This test must simulate the conditions in which the engine is
expected to operate in service, including typical start-stop cycles to establish when the
initial maintenance is required.
EVE.3391 - System and component tests.
The applicant must show that systems and components not adequately
substantiated as part of the endurance demonstration or other demonstrations will
perform their intended functions in all declared environmental and operating conditions.
EVE.3392 - Rotor locking demonstration
If shaft rotation is prevented by locking the rotor(s), the engine must
demonstrate:
(a) Reliable rotor locking performance;
(b) Reliable unlocking performance; and
(c) That no hazardous engine effects, as specified in EVE.3375(d)(2), will
occur.
EVE.3393 - Teardown inspection
The applicant must comply with either paragraph (a) or (b) of this section as
follows:
(a) Teardown evaluation.
(1) After the endurance and durability demonstrations have been completed,
the engine must be completely disassembled. Each engine component and lubricant must
be eligible for continued operation in accordance with the information submitted for
showing compliance with EVE.1529.
(2) Each engine component having an adjustment setting and a functioning
characteristic that can be established independent of installation on or in the engine must
retain each setting and functioning characteristic within the established and recorded limits
at the beginning of the endurance and durability demonstrations.
(b) Non-Teardown evaluation.
If a teardown cannot be performed for all engine components in a non-
destructive manner, then the inspection or replacement intervals for these components
and lubricants must be established based on the endurance and durability demonstrations
and documented in the ICA in accordance with EVE.1529.
EVE.3394 - Containment
The engine must be designed and constructed to protect against likely hazards
from rotating components as follows:
(a) The design of the case surrounding rotating components must provide for
the containment of the rotating components in the event of failure, unless the applicant
shows that the margin to rotor burst precludes the possibility of a rotor burst;
(b) If the margin to burst shows the case must have containment features in
the event of failure, the case must provide for the containment of the failed rotating
components. The applicant must define by test, validated analysis, or a combination
thereof, and document in the engine installation manual, the energy level, trajectory, and
size of fragments released from damage caused by the main rotor failure, and that pass
forward or aft of the surrounding case.
EVE.3399 - General conduct of tests.
(a) Maintenance of the engine may be made during the tests in accordance
with the service and maintenance instructions submitted in compliance with EVE.1529.
(b) The applicant must subject the engine or its parts to maintenance and
additional tests that ANAC finds necessary if:
(1) The frequency of the service is excessive;
(2) The number of stops due to engine malfunction is excessive;
(3) Major repairs are needed; or
(4) Replacement of a part is found necessary during the tests or due to the
teardown inspection findings.
(c) Upon completion of all demonstrations and testing specified in these
airworthiness criteria, the engine and its components must be:
(1) Within serviceable limits;
(2) Safe for continued operation; and
(3) Capable of operating at declared ratings while remaining within limits.
EVE.33100 - Engine electrical systems.
(a) Applicability. Any system or device that provides, uses, conditions, or
distributes electrical power, and is part of the engine type design, must provide for the
continued airworthiness of the engine and maintain electric engine ratings.
(b) Electrical systems. The electrical system must ensure the safe generation
and transmission of power, electrical load shedding, and the engine does not experience
any unacceptable operating characteristics or exceed its operating limits.
(c) Electrical-power distribution.
(1) The engine electrical-power distribution system must be designed to provide
the safe transfer of electrical energy throughout the electrical power plant. The system
must be designed to provide electrical power so that the loss, malfunction, or interruption
of the electrical power source will not result in a hazardous engine effect, as defined in
EVE.3375(g)(2).
(2) The system must be designed and maintained to withstand normal and
abnormal conditions during all ground and flight operations
(3) The system must provide mechanical or automatic means to mitigate a
faulted electrical-energy generation or storage device from leading to hazardous engine
effects, as defined in EVE.3375(g)(2), or detrimental effects in the intended aircraft
application.
(d) Protection systems. The engine electrical system must be designed such that
the loss, malfunction, interruption of the electrical power source, or power conditions that
exceed design limits will not result in hazardous engine effects, as defined in
EVE.3375(g)(2)).
(e) Electrical Power Characteristics. The applicant must identify and declare, in
the engine installation manual, the characteristics of any electrical power supplied from-
(1) The aircraft to the engine electrical system, for starting and operating the
engine, including transient and steady-state voltage limits, or
(2) The engine to the aircraft via energy regeneration, and any other
characteristics necessary for safe operation of the engine.
(f) Environmental limits. Environmental limits that cannot be adequately
substantiated by endurance demonstration, validated analysis, or a combination thereof
must be demonstrated by the system and component tests in EVE.3391.
(g) Electrical-system failures. The engine electrical system must:
(1) Have a maximum rate of Loss of Power Control (LOPC) that is suitable for
the intended aircraft application;
(2) When in the full-up configuration, be single fault tolerant, as determined by
ANAC, for electrical, electrically detectable, and electronic failures involving LOPC events;
(3) Not have any single failure that results in hazardous engine effects; and
(4) Not have any likely failure or malfunction that leads to local events in the
intended aircraft application.
(h) System-safety assessment. The applicant must perform a system-safety
assessment. This assessment must identify faults or failures that affect normal operation,
together with the predicted frequency of occurrence of these faults or failures. The
intended aircraft application must be taken into account to assure the assessment of the
engine system safety is valid.
EVE.1529 Instructions for Continued Airworthiness
The applicant must prepare Instructions for Continued Airworthiness (ICA), in
accordance with Appendices A and A1 that are acceptable to ANAC. ICA for the aircraft and
engines may be shown in a single aircraft ICA manual if the engine approval is sought
through the aircraft certification program. Alternatively, the applicant may provide
individual ICA for the aircraft and engines. The instructions may be incomplete at the time
of type certification if a program exists to ensure their completion prior to delivery of the
first aircraft, or issuance of a standard certificate of airworthiness, whichever occurs later.
Appendix A - Instructions for Continued Airworthiness
EVE.A.1 - General
(a) This appendix specifies requirements for the preparation of Instructions for
Continued Airworthiness as required by this regulation.
(b) The Instructions for Continued Airworthiness for each aircraft must include
the Instructions for Continued Airworthiness for each engine and propeller (hereinafter
designated "products"), for each appliance required by ANAC, and any required
information relating to the interface of those appliances and products with the aircraft. If
Instructions for Continued Airworthiness are not supplied by the manufacturer of an
appliance or product installed in the aircraft, the Instructions for Continued Airworthiness
for the aircraft must include the information essential to the continued airworthiness of
the aircraft.
(c) The applicant must submit to ANAC a program to show how changes to the
Instructions for Continued Airworthiness made by the applicant or by the manufacturers of
products and appliances installed in the aircraft will be distributed.
EVE.A.2 - Format
(a) The Instructions for Continued Airworthiness must be in the form of a
manual or manuals as appropriate for the quantity of data to be provided.
(b) The format of the manual or manuals must provide for a practical
arrangement.
EVE.A.3 - Content
The contents of the manual or manuals must be prepared in the English or
Portuguese language. The Instructions for Continued Airworthiness must contain the
following manuals or sections and information:
(a) aircraft maintenance manual or section.
(1) Introduction information that includes an explanation of the aircraft's
features and data to the extent necessary for maintenance or preventive maintenance.
(2) A description of the aircraft and its systems and installations including its
engines, propellers, and appliances.
(3) Basic control and operation information describing how the aircraft
components and systems are controlled and how they operate, including any special
procedures and limitations that apply.
(4) Servicing information that covers details regarding servicing points,
capacities of tanks, reservoirs, types of fluids to be used, pressures applicable to the
various systems, location of access panels for inspection and servicing, locations of
lubrication points, lubricants to be used, equipment required for servicing, tow instructions
and limitations, mooring, jacking, and leveling information.
(b) Maintenance Instructions.
(1) Scheduling information for each part of the aircraft and its engines, auxiliary
power units, propellers, accessories, instruments, and equipment that provides the
recommended periods at which they should be cleaned, inspected, adjusted, tested, and
lubricated, and the degree of inspection, the applicable wear tolerances, and work
recommended at these periods. However, the applicant may refer to an accessory,
instrument, or equipment manufacturer as the source of this information if the applicant
shows that the item has an exceptionally high degree of complexity requiring specialized
maintenance techniques, test equipment, or expertise. The recommended overhaul periods
and necessary cross-reference to the Airworthiness Limitations section of the manual must
also be included. In addition, the applicant must include an inspection program that
includes the frequency and extent of the inspections necessary to provide for the
continued airworthiness of the aircraft.
(2) Troubleshooting information describing probable malfunctions, how to
recognize those malfunctions, and the remedial action for those malfunctions.
(3) Information describing the order and method of removing and replacing
products and parts with any necessary precautions to be taken.
(4) Other general procedural instructions including procedures for system
testing during ground running, symmetry checks, weighing and determining the center of
gravity, lifting and shoring, and storage limitations.
(c) Diagrams of structural access plates and information needed to gain access
for inspections when access plates are not provided.
(d) Details for the application of special inspection techniques including
radiographic and ultrasonic testing where such processes are specified by the applicant.
(e) Information needed to apply protective treatments to the structure after
inspection.
(f) All data relative to structural fasteners such as identification, discard
recommendations, and torque values.
(g) A list of special tools needed.
(h) Reserved
EVE.A.4 - Airworthiness limitations section
The Instructions for Continued Airworthiness must contain a section titled
Airworthiness Limitations that is segregated and clearly distinguishable from the rest of the
document. This section must set forth each mandatory replacement time, structural
inspection interval, and related structural inspection procedure required for type
certification. If the Instructions for Continued Airworthiness consist of multiple documents,
the section required by this paragraph must be included in the principal manual. This
section must contain a legible statement in a prominent location that reads "The
Airworthiness Limitations section is ANAC approved and specifies maintenance required
under section 43.16 of RBAC 43 and under section 91.403 of RBAC 91 unless an alternative
program has been ANAC approved."
Appendix A1 - Instructions for Continued Airworthiness (Electric Engine)
EVE.A.33.1 - General.
(a) This appendix specifies requirements for the preparation of ICA for the
engines as required by EVE.1529.
(b) The ICA for the engine must include the ICA for all engine parts.
(c) The applicant must submit to ANAC a program to show how the applicant's
changes to the ICA will be distributed, if applicable.
EVE.A.33.2 - Format
(a) The Instructions for Continued Airworthiness must be in the form of a
manual or manuals as appropriate for the quantity of data to be provided.
(b) The format of the manual or manuals must provide for a practical
arrangement.
EVE.A.33.3 - Content
The contents of the manual or manuals must be prepared in the English
language. The Instructions for Continued Airworthiness must contain the following manuals
or sections, as appropriate, and information:
(a) Engine Maintenance Manual or Section.
(1) Introduction information that includes an explanation of the engine's
features and data to the extent necessary for maintenance or preventive maintenance.
(2) A detailed description of the engine and its components, systems, and
installations.
(3) Installation instructions, including proper procedures for uncrating, deinhibiting,
acceptance checking, lifting, and attaching accessories, with any necessary checks.
(4) Basic control and operating information describing how the engine
components, systems, and installations operate, and information describing the methods of
starting, running, testing, and stopping the engine and its parts including any special
procedures and limitations that apply.
(5) Servicing information that covers details regarding servicing points,
capacities of tanks, reservoirs, types of fluids to be used, pressures applicable to the
various systems, locations of lubrication points, lubricants to be used, and equipment
required for servicing.
(6) Scheduling information for each part of the engine that provides the
recommended periods at which it should be cleaned, inspected, adjusted, tested, and
lubricated, and the degree of inspection the applicable wear tolerances, and work
recommended at these periods. However, the applicant may refer to an accessory,
instrument, or equipment manufacturer as the source of this information if the applicant
shows that the item has an exceptionally high degree of complexity requiring specialized
maintenance techniques, test equipment, or expertise. The recommended overhaul periods
and necessary cross references to the Airworthiness Limitations section of the manual
must also be included. In addition, the applicant must include an inspection program that
includes the frequency and extent of the inspections necessary to provide for the
continued airworthiness of the engine.
(7) Troubleshooting information describing probable malfunctions, how to
recognize those malfunctions, and the remedial action for those malfunctions.
(8) Information describing the order and method of removing the engine and its
parts and replacing parts, with any necessary precautions to be taken. Instructions for
proper ground handling, crating, and shipping must also be included.
(9) A list of the tools and equipment necessary for maintenance and directions
as to their method of use.
(b) Engine Overhaul Manual or Section.
(1) Disassembly information including the order and method of disassembly for overhaul.
(2) Cleaning and inspection instructions that cover the materials and apparatus
to be used and methods and precautions to be taken during overhaul. Methods of
overhaul inspection must also be included.
(3) Details of all fits and clearances relevant to overhaul.
(4) Details of repair methods for worn or otherwise substandard parts and
components along with the information necessary to determine when replacement is necessary.
(5) The order and method of assembly at overhaul.
(6) Instructions for testing after overhaul.
(7) Instructions for storage preparation, including any storage limits.
(8) A list of tools needed for overhaul.
(c) Reserved.
EVE.A.33.4 - Airworthiness limitations section
The Instructions for Continued Airworthiness must contain a section titled Airworthiness
Limitations that is segregated and clearly distinguishable from the rest of the manual.
(a) For all engines:
(1) The Airworthiness Limitations section must set forth each mandatory
replacement time, inspection interval, and related procedure required for type
certification. If the Instructions for Continued Airworthiness consist of multiple documents,
the section required under this paragraph must be included in the principal manual.
(2) This section must contain a legible statement in a prominent location that
reads: "The Airworthiness Limitations section is approved and specifies maintenance
required under RBAC 43 and RBAC 91 unless an alternative program has been approved."
(b) Reserved.