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Federal Register / Vol. 86, No. 184 / Monday, September 27, 2021 / Rules and Regulations
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 Special Condition no. 17d2 of these special conditions.
2 Life-limited part means a rotor and major structural static part, the failure of which can result in a hazardous engine effect due to low-cycle fatigue LCF
mechanism or any LCF driven mechanism coupled with creep. 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 Administrator the following three plans for approval:
1 An engineering plan that establishes and maintains that the combination of loads, material properties, environmental influences, and operating conditions, including the effects of engine parts influencing these parameters, are sufficiently well-known and predictable by validated analysis, test, or service experience. The engineering plan must ensure each critical part or life-limited part is withdrawn from service at an approved life before hazardous engine effects can occur. The engineering plan must establish activities to be executed both preand post-certification. In addition to the activities that must be completed prior to certification, including a reporting system that flows, back to magniX, problematic issues that develop in engines while they operate in-service, to be addressed by the design process.
magniX must perform appropriate damage-tolerance assessments to address the potential for failure from material, manufacturing, and serviceinduced anomalies within the approved life of the part. The approved life must be published in the mandatory ICA.
2 A manufacturing plan that identifies the specific manufacturing definition drawings, procedures, specifications, etc. necessary for the manufacturer to consistently produce critical or life-limited parts with the design attributes required by the engineering plan.
3 A service-management plan defines in-service processes for maintenance and repair of critical or life-limited parts that maintain
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attributes consistent with those required by the engineering plan. These processes must be part of the mandatory ICA.
14. Lubrication System a The lubrication system must be designed and constructed to function properly between scheduled maintenance intervals in all flight attitudes and atmospheric conditions in which the engine is expected to operate.
b The lubrication system must be designed to prevent contamination of the engine bearings and lubrication system components.
c The applicant must demonstrate by test, validated analysis, or a combination thereof, the unique lubrication attributes and functional capability of a and b.
15. Power Response The design and construction of the engine, including its control system, must enable an increase a From the minimum power setting to the highest-rated power without detrimental engine effects;
b 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 safe for aircraft operation; and c From the minimum torque to the highest-rated torque without detrimental engine or aircraft effects to ensure aircraft structural integrity or aircraft aerodynamic characteristics are not exceeded.
16. 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 any hazardous engine effects, as specified in Special Condition no. 17d2.
17. Safety Analysis a The applicant must comply with 33.75a1 and a2 using the failure definitions in Special Condition no.
17d.
b If the failure of such elements is likely to result in hazardous engine effects, then the applicant may show compliance by reliance on the prescribed integrity requirements such as 33.15, Special Condition no. 9, Special Condition no. 13, or combinations thereof, as applicable. The failure of such elements and associated prescribed integrity requirements must be stated in the safety analysis.
c The applicant must comply with 33.75d and e using the failure definitions in Special Condition no.
17d of these special conditions.

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d Unless otherwise approved by the Administrator, the following definitions apply to the engine effects when showing compliance with this condition:
1 A minor engine effect does not prohibit the engine from meeting its certificated performance requirements and the intended functions in a manner consistent with 33.28b1i, 33.28b1iii and 33.28 b1iv, and the engine complies with the operability requirements such as Special Condition no. 15 Power response, Special Condition no. 25 Operation demonstration, and Special Condition no. 31 Operation with a variable pitch propeller, as appropriate.
2 The engine effects in 33.75g2
are hazardous engine effects with the addition of:
i Electrocution of the crew, passengers, operators, maintainers, or others; and ii Blockage of cooling systems that are required for the engine to operate within temperature limits.
3 Any other engine effect is a major engine effect.
e The intended aircraft application must be taken into account to assure the analysis of the engine system safety is valid.
18. Ingestion a Ingestion from likely sources foreign objects, birds, ice, hail must not result in hazardous engine effects defined by Special Condition no.
17d2, or unacceptable power loss.
b Rain ingestion must not result in an abnormal operation such as shutdown, power loss, erratic operation, or power oscillations throughout the engine operating range.
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 following potential ingestion, then the features, attachments, or systems must be documented in the engine installation manual.
d Ingestion sources that are not evaluated must be declared in the engine installation manual.
19. Liquid Systems a Each liquid system used for lubrication or cooling of engine components must be designed and constructed to function properly in all flight attitudes and atmospheric conditions in which the engine is expected to operate.
b If a liquid system used for lubrication or cooling of engine components is not self-contained, the
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