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.

(c) Safety analysis assumptions. The assumptions of the safety analysis as described in EVE.3375(d) with respect to the reliability of safety devices, instrumentation, early warning devices, maintenance checks, and similar equipment or procedures that are outside the control of the engine manufacturer.

EVE.3307 - Engine ratings and operating limits.

(a) Engine ratings and operating limitations are established by ANAC and included in the engine certificate data sheet specified in RBAC 21.41, including ratings and limitations based on the operating conditions and information specified in this section, as applicable, and any other information found necessary for safe operation of the engine.

(b) For electric engines, ratings and operating limits are established relating to the following:

(1) Shaft power, torque, rotational speed, and temperature for:

(i) Rated takeoff power;

(ii) Rated maximum continuous power; and

(ii) Rated maximum temporary power and associated time limit.

(2) Duty cycle and the rating at that duty cycle. The duty cycle must be declared in the type certificate data sheet or documented in the engine installation manual.

(3) Reserved.

(4) Power-supply requirements.

(5) Any other ratings or limitations that are necessary for the safe operation of the engine.

(c) In determining the engine performance and operating limitations, the overall limits of accuracy of the engine control system, of the engine electrical systems, and of the necessary instrumentation as defined in EVE.3305(a)(6) must be taken into account.

EVE.3308 - Selection of Engine Power and Thrust Ratings

(a) Requested engine power and thrust ratings must be selected by the applicant.

(b) Each selected rating must be for the lowest power or thrust that all engines of the same type may be expected to produce under the conditions used to determine that rating.

EVE.3315 - Materials

(a) Be established on the basis of experience or tests; and

(b) Conform to approved specifications (such as industry or military specifications) that ensure their having the strength and other properties assumed in the design data.

EVE.3317 - Fire protection

(a) The design and construction of the engine and the materials used must minimize the probability of the occurrence and spread of fire during normal operation and failure conditions, and must minimize the effect of such a fire. In addition, the design and construction of electrical engines must minimize the probability of the occurrence of an internal fire that could result in structural failure or other hazardous effects.

EVE.3318 - High-Voltage EWIS arc fault protection

(a) High-voltage EWIS must be protected against arc faults that can lead to hazardous engine effects as defined in EVE.3375(g)(2). Any non-protected electrical wiring interconnections must be analyzed to show that arc faults do not cause a hazardous engine effect.EVE.3319 - Durability.

The engine design and construction must minimize the development of an unsafe condition of the engine between maintenance intervals, overhaul periods, or mandatory actions described in the applicable ICA.

EVE.3321 - Engine cooling.

Engine design and construction must provide the necessary cooling under conditions in which the aircraft is expected to operate. If cooling is required to satisfy the safety analysis as described in EVE.3375, the cooling system monitoring features and usage must be documented in the engine installation manual.

EVE.3323 - Engine Mounting Attachment and Structure

(a) The maximum allowable limit and ultimate loads for engine mounting attachments and related engine structure must be specified.

(b) The engine mounting attachments and related engine structure must be able to withstand:

(1) The specified limit loads without permanent deformation; and

(2) The specified ultimate loads without failure,but may exhibit permanent deformation.

EVE.3325 - Accessory Attachments

The engine must operate properly with the accessory drive and mounting attachments loaded. Each engine accessory drive and mounting attachment must include provisions for sealing to prevent contamination of, or unacceptable leakage from, the engine interior. A drive and mounting attachment requiring lubrication for external drive splines, or coupling by engine oil, must include provisions for sealing to prevent unacceptable loss of oil and to prevent contamination from sources outside the chamber enclosing the drive connection. The design of the engine must allow for the examination, adjustment, or removal of each accessory required for engine operation.

EVE.3327 - Overspeed

(a) A rotor overspeed must not result in a burst, rotor growth, or damage that results in a hazardous engine effect, as defined in EVE.3375(g)(2). Compliance with this paragraph must be shown by test, validated analysis, or a combination of both. Applicable assumed rotor speeds must be declared and justified.

(b) Rotors must possess sufficient strength with a margin to burst above certified operating conditions and above failure conditions leading to rotor overspeed. The margin to burst must be shown by test, validated analysis, or a combination thereof.

(c) The engine must not exceed the rotor-speed operational limitations that could affect rotor structural integrity.

EVE.3328 - Engine control systems.

(a) Applicability. - These requirements apply to any system or device that is part of the engine type design that controls, limits, monitors, or protects engine operation and is necessary for the continued airworthiness of the engine.

(b) Engine control. - The engine control system must ensure the engine does not experience any unacceptable operating characteristics or exceed its operating limits, including in failure conditions where the fault or failure results in a change from one control mode to another, from one channel to another, or from the primary system to the back-up system, if applicable.

(c) Design assurance. The software and complex electronic hardware, including programmable logic devices, must be:

(1) Designed and developed using a structured and systematic approach that provides a level of assurance for the logic commensurate with the hazard associated with the failure or malfunction of the systems in which the devices are located; and

(2) Substantiated by a verification methodology acceptable to ANAC.

(d) Validation. All functional aspects of the control system must be substantiated by test, analysis, or a combination thereof, to show that the engine control system performs the intended functions throughout the approved flight envelope.

(e) 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.

(f) Engine control system failures. The engine control system must:

(1) Have a maximum rate of Loss of Power Control (LOPC) that is suitable for the intended aircraft application. The estimated LOPC rate must be specified in the engine installation manual;

(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 as defined in EVE.3375(g)(2); and

(4) Ensure failures or malfunctions that lead to local events in the aircraft do not result in hazardous engine effects as defined in EVE.3375(g)(2) due to engine control system failures or malfunctions.

(g) 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 control system safety is valid. The rates of hazardous and major faults must be declared in the engine installation manual.

(h) Protection systems. The engine control devices and systems' design and function, together with engine instruments, operating instructions, and maintenance instructions, must ensure that engine operating limits that can lead to a hazard will not be exceeded in-service.

(i) Aircraft-supplied data. Any single failure leading to loss, interruption, or corruption of aircraft-supplied data (other than power command signals from the aircraft), or aircraft-supplied data shared between engine systems within a single engine or between fully independent engine systems, must:

(1) Not result in a hazardous engine effect, as defined in EVE.3375(g)(2), for any engine installed on the aircraft; and

(2) Be able to be detected and accommodated by the control system.

(j) Engine control system electrical power.(1) The engine control system must be designed such that the loss, malfunction, or interruption of the control system electrical power source will not result in a hazardous engine effect, as defined in EVE.3375(g)(2), the unacceptable transmission of erroneous data, or continued engine operation in the absence of the control function. The engine control system must be capable of resuming normal operation when aircraft-supplied power returns to within the declared limits.

(2) The applicant must identify and declare, in the engine installation manual, the characteristics of any electrical power supplied from the aircraft to the engine control system, including transient and steady-state voltage limits, and any other characteristics necessary for safe operation of the engine.

EVE.3329 - Instrument connection.

(a) Unless it is constructed to prevent its connection to an incorrect instrument, each connection provided for powerplant instruments required by aircraft airworthiness regulations or necessary to insure operation of the engine in compliance with any engine limitation must be marked to identify it with its corresponding instrument.

(b) In addition, as part of the system-safety assessment of EVE.3328(g) and EVE.33100(h), the applicant must assess the possibility and subsequent effect of incorrect fit of instruments, sensors, or connectors. Where practicable, the applicant must take design precautions to prevent incorrect configuration of the system.

(c) The applicant must make provision for the installation of instrumentation necessary to ensure operation in compliance with engine operating limitations. Where, in presenting the safety analysis, or complying with any other requirement, dependence is placed on instrumentation that is not otherwise mandatory in the assumed aircraft installation, then the applicant must specify this instrumentation in the engine installation instructions and declare it mandatory in the engine approval documentation.

(d) The applicant must provide instrumentation enabling the flightcrew to monitor the functioning of the engine cooling system unless evidence shows that:

(1) Other existing instrumentation provides adequate warning of failure or impending failure;

(2) Failure of the cooling system would not lead to hazardous engine effects, as defined in EVE.3375(g)(2), before detection; or

(3) The probability of failure of the cooling system is extremely remote.

(e) The sensors, together with associated wiring and signal conditioning, must be segregated, electrically and physically, to the extent necessary to ensure that the probability of a fault propagating from instrumentation and monitoring functions to control functions, or vice versa, is consistent with the failure effect of the fault.

EVE.3362 - Stress analysis.

(a) A mechanical and thermal stress analysis, as well as the stress caused by electromagnetic forces, must show a sufficient design margin to prevent unacceptable operating characteristics and hazardous engine effects as defined in EVE.3375(g)(2).

(b) Maximum stresses in the engine must be determined by test, validated analysis, or a combination thereof, and must be shown not to exceed minimum material properties."

EVE.3363 - Vibration

(a) The engine must be designed and constructed to function throughout its normal operating range of rotor speeds and engine output power, including defined exceedances, without inducing excessive stress in any of the engine parts because of vibration and without imparting excessive vibration forces to the aircraft structure.

(b) Each engine design must undergo a vibration survey to establish that the vibration characteristics of those components subject to induced vibration are acceptable throughout the declared flight envelope and engine operating range for the specific installation configuration. The possible sources of the induced vibration that the survey must assess are mechanical, aerodynamic, acoustical, internally induced electromagnetic, installation induced effects that can affect the engine vibration characteristics, and likely environmental effects. This survey must be shown by test, validated analysis, or a combination thereof.

EVE.3370 - Critical and life-limited parts.

(a) The applicant must show, by a safety analysis or means acceptable to the ANAC, whether rotating or moving components, bearings, shafts, static parts, and non- redundant mount components should be classified, designed, manufactured, and managed throughout their service life as critical or life-limited parts.

(1) Critical part means a part that must meet prescribed integrity specifications to avoid its primary failure, which is likely to result in a hazardous engine effect as defined in EVE.3375(g)(2).

(2) Life-limited parts may include but are not limited to a rotor and major structural static part, the failure of which can result in a hazardous engine effect, as defined in EVE.3375(g)(2), due to low-cycle fatigue (LCF) mechanism. A life limit is an operational limitation that specifies the maximum allowable number of flight cycles that a part can endure before the applicant must remove it from the engine.

(b) In establishing the integrity of each critical part or life-limited part, the applicant must provide to the ANAC the following three plans for approval:(1) An engineering plan that contains the steps required to ensure each engine life-limited part is withdrawn from service at an approved life before hazardous engine effects can occur. In addition, the engineering plan must contain the steps to ensure each engine critical part is withdrawn from service before hazardous engine effects can occur. These steps include validated analysis, test, or service experience which ensures that the combination of loads, material properties, environmental influences and operating conditions, including the effects of other engine parts influencing these parameters, are sufficiently well known and predictable so that the operating limitations can be established and maintained for each engine life- limited and critical part. Applicants must perform appropriate damage tolerance assessments to address the potential for failure from material, manufacturing, and service induced anomalies within the approved life of the part. Applicants must publish a list of the life-limited engine parts and the approved life for each part in the Airworthiness Limitations Section of the Instructions for Continued Airworthiness as required by EVE.1529.

(2) A manufacturing plan that identifies the specific manufacturing constraints necessary to consistently produce each engine life-limited and critical part with the attributes required by the engineering plan.

(3) A service management plan that defines in-service processes for maintenance and the limitations to repair for each engine life-limited and critical part that will maintain attributes consistent with those required by the engineering plan. These processes and limitations will become part of the Instructions for Continued Airworthiness.

EVE.3373 - Power response.

(a) The design and construction of the engine, including its control system, must enable an increase-

(1) From the minimum power setting to the highest rated power without detrimental engine effects in the intended aircraft application;

(2) From the minimum obtainable power while in flight, and while on the ground, to the highest rated power within a time interval determined to be appropriate for the intended aircraft application; and

(3) From the minimum torque to the highest rated torque without detrimental engine effects in the intended aircraft application.

(b) The results of the increases in paragraphs (a)(1), (a)(2), and (a)(3) of this section must be included in the engine installation manual.

EVE.3374 - Continued rotation.

If the design allows any of the engine main rotating systems to continue to rotate after the engine is shut down while in-flight, this continued rotation must not result in hazardous engine effects, as specified in EVE.3375(g)(2).

EVE.3375 - Safety Analysis

(a)(1) The applicant must analyze the engine, including the control system, to assess the likely consequences of all failures that can reasonably be expected to occur. This analysis will take into account, if applicable:

(i) Aircraft-level devices and procedures assumed to be associated with a typical installation. Such assumptions must be stated in the analysis.

(ii) Consequential secondary failures and latent failures.

(iii) Multiple failures referred to in paragraph (d) of this section or that result in the hazardous engine effects defined in paragraph (g)(2) of this section.

(2) The applicant must summarize those failures that could result in major engine effects or hazardous engine effects, as defined in paragraph (g) of this section, and estimate the probability of occurrence of those effects. Any engine part the failure of which could reasonably result in a hazardous engine effect must be clearly identified in this summary.

(b) The applicant must comply with paragraphs (a)(1) and (a)(2) of this section using the failure definitions in paragraph (g) of this section and ICA in EVE.1529.

(c) The primary failure of certain single elements cannot be sensibly estimated in numerical terms. If the failure of such elements is likely to result in hazardous engine effects, then compliance may be shown by reliance on the prescribed integrity requirements such as EVE.3315, EVE.3327, EVE.3370, or combinations thereof, as applicable. These instances must be stated in the safety analysis.

(d) If reliance is placed on a safety system to prevent a failure from progressing to hazardous engine effects, the possibility of a safety system failure in combination with a basic engine failure must be included in the analysis. Such a safety system may include safety devices, instrumentation, early warning devices, maintenance checks, and other similar equipment or procedures. If items of a safety system are outside the control of the engine manufacturer, the assumptions of the safety analysis with respect to the reliability of these parts must be clearly stated in the analysis and identified in the installation instructions under EVE.3305.

(e) If the safety analysis depends on one or more of the following items, those items must be identified in the analysis and appropriately substantiated.

(1) Maintenance actions being carried out at stated intervals. This includes the verification of the serviceability of items that could fail in a latent manner. When necessary to prevent hazardous engine effects, these maintenance actions and intervals must be published in the ICA required under EVE.1529. Additionally, if errors in maintenance of the engine, including the control system, could lead to hazardous engine effects, the appropriate procedures must be included in the relevant engine manuals.

(2) Verification of the satisfactory functioning of safety or other devices at pre-flight or other stated periods. The details of this satisfactory functioning must be published in the appropriate manual.

(3) The provisions of specific instrumentation not otherwise required.

(4) Flight crew actions to be specified in the operating instructions established under EVE.3305.

(f) The applicant must comply with paragraphs (d) and (e) of this section using the failure definitions in paragraph (g) of this section.

(g) Unless otherwise approved by ANAC and stated in the safety analysis, the following failure definitions apply to the engine:

(1) A minor engine effect does not prohibit the engine from meeting its type-design requirements and the intended functions in a manner consistent with (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this section, and the engine complies with the operability requirements such as EVE.3373 and EVE.3389, as appropriate, or does not result in LOPC.

(i) Enables selected values of relevant control parameters to be maintained and the engine kept within the approved operating limits over changing atmospheric conditions in the approved flight envelope;

(ii) Allows modulation of engine power or thrust with adequate sensitivity over the declared range of engine operating conditions; and

(iii) Does not create unacceptable power or thrust oscillation."

(2) The following effects will be regarded as hazardous engine effects:

(i) Non-containment of high-energy debris;

(ii) Reserved.

(iii) Significant thrust in the opposite direction to that commanded by the pilot;

(iv) Uncontrolled fire;

(v) Failure of the engine mount system leading to inadvertent engine separation;

(vi) Release of the propeller by the engine, if applicable;

(vii) Complete inability to shut the engine down;

(viii) Electrocution of the crew, passengers, operators, maintainers, or others; and

(ix) Reserved.

(h) The intended aircraft application must be taken into account when performing the safety analysis.

(i) The results of the safety analysis and the assumptions about the aircraft application used in the safety analysis must be documented in the engine installation manual.

EVE.3377 - Ingestion

(a) Rain, ice and hail ingestion must not result in an abnormal operation such as shutdown, power loss, erratic operation, or power oscillations throughout the engine operating range.

(b) Ingestion from other likely sources (birds, induction system ice, hailstones, foreign objects- ice slabs) must not result in hazardous engine effects, as defined in EVE.3375(g)(2), or unacceptable power loss.

(c) If the design of the engine relies on features, attachments, or systems that the installer may supply, for the prevention of unacceptable power loss or hazardous engine effects as defined in EVE.3375(g)(2) following potential ingestion, then the features, attachments, or systems must be documented in the engine installation manual.

EVE.3384 - Engine overtorque test.

When approval is sought for a transient maximum engine overtorque, the applicant must demonstrate by test, validated analysis, or a combination thereof, that the engine can continue operation after operating at the maximum engine overtorque condition without maintenance action. Upon conclusion of overtorque tests conducted to show compliance with this subpart, or any other tests that are conducted in combination with the overtorque test, each engine part or individual groups of components must meet the requirements of EVE.3393.

EVE.3385 - Calibration Test

Each engine must be subjected to calibration tests to establish its power characteristics and the conditions both before and after the endurance and durability demonstrations specified in EVE.3387 and EVE.3390.

EVE.3387 - Endurance Demonstration

(a) The applicant must subject the engine to an endurance demonstration, acceptable to ANAC, to demonstrate the engine's limit capabilities.

(b) The endurance demonstration must include increases and decreases of the engine's power settings, energy regeneration, and dwellings at the power settings or energy regeneration for durations that produce the extreme physical conditions the engine experiences at rated performance levels, operational limits, and at any other conditions or power settings that are required to verify the limit capabilities of the engine.

EVE.3388 - Temperature Limit.

The engine design must demonstrate its capability to endure operation at its temperature limits plus an acceptable margin. The applicant must quantify and justify to ANAC the margin. The demonstration must be repeated for all declared duty cycles and ratings, and operating environments, that would impact temperature limits.

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.