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lotter on DSK11XQN23PROD with RULES3

Federal Register / Vol. 86, No. 184 / Monday, September 27, 2021 / Rules and Regulations
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interfaces to that system must be defined in the engine installation manual.
c The applicant must establish by test, validated analysis, or a combination of both that all static parts subject to significant gas or liquid pressure loads will not:
1 Exhibit permanent distortion beyond serviceable limits or exhibit leakage that could create a hazardous condition when subjected to normal and maximum working pressure with margin.
2 Exhibit fracture or burst when subjected to the greater of maximum possible pressures with margin.
d Compliance with Special Condition no. 19c must take into account:
1 The operating temperature of the part;
2 Any other significant static loads in addition to pressure loads;
3 Minimum properties representative of both the material and the processes used in the construction of the part; and 4 Any adverse physical geometry conditions allowed by the type design, such as minimum material and minimum radii.
e Approved coolants and lubricants must be listed in the engine installation manual.

without maintenance action. Upon conclusion of overtorque tests conducted to show compliance with this special condition, 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 Special Condition no. 29.

engine is expected to operate in-service, including typical start-stop cycles.

22. Calibration Assurance
28. Rotor Locking Demonstration
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 Special Conditions nos. 23 and 26.

If shaft rotation is prevented by locking the rotors, the engine must demonstrate:
a Reliable rotor locking performance;
b Reliable unlocking performance;
and c That no hazardous engine effects, as specified in Special Condition no.
17d2, will occur.

20. Vibration Demonstration 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 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 that may be 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, or electromagnetic. This survey must be shown by test, validated analysis, or a combination thereof.

24. Temperature Limit
21. Overtorque 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
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23. Endurance Demonstration The applicant must subject the engine to an endurance demonstration, acceptable to the Administrator, to demonstrate the engines limit capabilities.
The endurance demonstration must include increases and decreases of the engines power settings, and dwellings at the power settings 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.
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 the Administrator the margin at each rated condition. The demonstration must be repeated for all declared duty cycles and associated ratings, and operating environments, that would impact temperature limits.
25. 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.
26. 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
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27. System and Component Tests The applicant must show that systems and components will perform their intended functions in all declared environmental and operating conditions.

29. Teardown Inspection The applicant must comply with either a or b 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 within service limits and eligible for continued operation in accordance with the information submitted for showing compliance with 33.4, Instructions for Continued Airworthiness.
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 is not performed for all engine components, then the life limits for these components and lubricants must be established based on the endurance and durability demonstrations and documented in the ICA in accordance with 33.4.
30. Containment The engine must provide containment features that 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 that the case must have containment features in the event of failure, the case must provide for the containment of the failed
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