--- title: "SUBPART E – TURBINE ENGINES: TYPE SUBSTANTIATION — CS-E — rule index · Avioverse" description: "SUBPART E – TURBINE ENGINES: TYPE SUBSTANTIATION (70 paragraphs), CS-E. All tests must be made with air intakes conforming to an acceptable design that…" url: "https://avioverse.aero/regulations/easa/cs-e/subpart-e" --- # SUBPART E – TURBINE ENGINES: TYPE SUBSTANTIATION Engines (CS-E) · CS-E 1. ## [CS-E 600 Tests - General](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-600-tests-general) All tests must be made with air intakes conforming to an acceptable design that is as representative of the powerplant intakes as is practicable. 2. ## [AMC E 600(e) Test - General](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-600-e-test-general) The applicant should justify any difference between the Engine attitude during the tests and the Engine attitude in the intended rotorcraft installations. 3. ## [CS-E 620 Performance Correction](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-620-performance-correction) (See AMC E 620) (a) All performance results must be corrected to the following assumed conditions of atmospheric pressure and temperature at mean sea… 4. ## [AMC E 620 Performance: Formulae](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-620-performance-formulae) The following corrections from the observed test conditions to the assumed atmospheric conditions of pressure and temperature should be used within the… 5. ## [CS-E 640 Pressure Loads](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-640-pressure-loads) (See AMC E 640) (a) Static Pressure Loads It must be established by test, validated analysis or combination thereof that all static parts which are… 6. ## [AMC E 640 Pressure Loads](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-640-pressure-loads) Definitions. For the purpose of CS-E 640(a) the following definitions apply and should be related to the Engine when installed in a typical installation. 7. ## [CS-E 650 Vibration Surveys](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-650-vibration-surveys) (See AMC E 650) (a) It must be established by test or a combination of test and validated analysis that the vibration characteristics of all components… 8. ## [AMC E 650 Vibration Surveys](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-650-vibration-surveys) Definitions. The following are defined for the purpose of this AMC: 9. ## [CS-E 660 Fuel Pressure and Temperature](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-660-fuel-pressure-and-temperature) (See AMC E 660) A substantiation must be made to establish the minimum and maximum fuel pressure and fuel temperature limits to be approved for the Engine. 10. ## [AMC E 660 Fuel Pump Tests (Turbine Engines for Aeroplanes)](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-660-fuel-pump-tests-turbine-engines-for-aeroplanes) When testing equipment susceptible to cavitation erosion (e.g. 11. ## [CS-E 670 Contaminated Fuel](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-670-contaminated-fuel) (See AMC E 670) (a) Evidence must be provided that the complete Engine fuel system is capable of functioning satisfactorily with fuel containing the… 12. ## [AMC E 670 Contaminated Fuel Testing](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-670-contaminated-fuel-testing) Solid Contaminants (a) A contaminant with the characteristics detailed in the following table is acceptable. 13. ## [CS-E 680 Inclination and Gyroscopic Load Effects](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-680-inclination-and-gyroscopic-load-effects) (See AMC E 680) It must be demonstrated that the effects of inclination on Engine running are not seriously detrimental and that the Engine is designed… 14. ## [AMC E 680 Inclination and Gyroscopic Load Effects](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-680-inclination-and-gyroscopic-load-effects) Normally inclination and gyroscopic load effects will be proved during flight testing but in certain cases some supplementary running or rig testing, to… 15. ## [CS-E 690 Engine Bleed](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-690-engine-bleed) (See AMC E 690) (a) For an Engine having bleed(s) for aircraft and/or Engine uses, the Engine endurance test schedule of CS-E 740 must be varied in… 16. ## [AMC E 690 Engine bleed](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-690-engine-bleed) For reducing test complexity, and for improved flexibility needed to attain the key parameters (speed, temperature and torque) during the 2-hour test of… 17. ## [CS-E 700 Excess Operating Conditions](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-700-excess-operating-conditions) (See AMC E 700) Where any of the operating conditions (e.g. air or gas pressure, thrust, gas temperature) substantiated elsewhere in this subpart could… 18. ## [AMC E 700 Excess Operating Conditions (Turbine Engines for Aeroplanes)](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-700-excess-operating-conditions-turbine-engines-for-aeroplanes) Case at VMO∗ (∗For light aeroplanes the speed VNE is normally used) The Engine should be run at the excess pressures and thrusts which would result from… 19. ## [CS-E 710 Rotor Locking Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-710-rotor-locking-tests) (See AMC E 710) If continued rotation is prevented by a means to lock the rotor(s), the Engine must be subjected to a test that includes 25 locking and… 20. ## [AMC E 710 Rotor locking tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-710-rotor-locking-tests) The applicant has the option to incorporate a rotor-locking device into the type design of the Engine in order not to have to comply with CS-E 525. 21. ## [CS-E 720 Continuous Ignition](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-720-continuous-ignition) Where approval of an Engine is sought which permits or requires the use of a continuously-operated ignition system, the specifications of CS-E 720(b)… 22. ## [AMC E 720(a) Continuous Ignition](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-720-a-continuous-ignition) The necessity for a continuously-operated system may arise, for example, in consideration of water or slush ingestion at take-off, ice ingestion, or for… 23. ## [CS-E 730 Engine Calibration Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-730-engine-calibration-test) (See AMC E 730) In order to identify the Engine thrust or power changes that may occur during the endurance test of CS-E 740, and to ensure that… 24. ## [AMC E 730 Calibration Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-730-calibration-tests) The parameters used for the calibration curves are those appropriate to, and compatible with, the Engine’s design. 25. ## [CS-E 740 Endurance Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-740-endurance-tests) ED Decision 208/014/R (a) The specifications of CS-E 740 must be varied and supplemented as necessary to comply with CS-E 690(a), CS-E 750 and CS-E 890. [AMC E 740(c)(4) Alternate Endurance Testing – Turbofan Engine](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-740-endurance-tests#amc-e-740-c-4) [AMC E 740(f)(5) Operating Limitations — Transient Engine rotor shaft over-speed, transient Engine exhaust gas over-temperature and transient Engine over-torque limit approval](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-740-endurance-tests#amc-e-740-f-5) 26. ## [AMC E 740(c)(2)(i) Endurance Tests – 30-Minute Power Rating](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-740-c-2-i-endurance-tests-30-minute-power-rating) For Rotorcraft turbine Engines to be approved with a 30-Minute Power rating: 27. ## [AMC E 740(c)(3) Endurance Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-740-c-3-endurance-tests) Two procedures for running the tests required under CS-E 740(c)(3) are acceptable: 28. ## [AMC E 740(f)(1) Multi-spool Engines](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-740-f-1-multi-spool-engines) Where an Endurance Test is conducted in accordance with CS-E 740(f)(1) supplementary evidence is required to substantiate any rotational speed… 29. ## [AMC E 740(g)(1) Endurance Tests - Incremental Periods](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-740-g-1-endurance-tests-incremental-periods) As an alternative to revising the incremental running as indicated in CS-E 740(g)(1), separate Engine running of appropriate severity may be completed… 30. ## [AMC E 740(i)(2) Endurance tests - Inspection checks](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-740-i-2-endurance-tests-inspection-checks) If relevant, the level of Engine disassembly, component cleaning and replacement prior to rebuild for the additional endurance test sequence should be… 31. ## [CS-E 745 Engine Acceleration](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-745-engine-acceleration) (See AMC E 745) (a) It must be demonstrated, on a test bed, that: 32. ## [AMC E 745 Engine Acceleration](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-745-engine-acceleration) Compliance with CS-E 745 may be demonstrated during tests performed to meet other sections of CS-E. 33. ## [CS-E 750 Starting Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-750-starting-tests) Twenty-five cold starts (i.e. after the Engine has been stopped for not less than two hours) and ten hot starts (i.e. 34. ## [AMC E 750(b) Starting tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-750-b-starting-tests) The «declared drainage period» after a false start referred to in CS-E 750(b) is the minimum period necessary to allow surplus fuel to drain from the… 35. ## [CS-E 770 Low Temperature Starting Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-770-low-temperature-starting-tests) (See AMC E 770) (a) The Engine must be shown to be capable of satisfactory starting and acceleration from the appropriate minimum temperatures declared… 36. ## [AMC E 770 Low Temperature Starting Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-770-low-temperature-starting-tests) It is normally acceptable in each of the tests of CS-E 770(b) and (c) to allow the Engine to inspire uncooled intake air. 37. ## [CS-E 780 Icing Conditions](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-780-icing-conditions) (See AMC E 780) (a)(1) It must be established by tests, unless alternative appropriate evidence is available, that the Engine will function… 38. ## [AMC E 780 Icing Conditions](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-780-icing-conditions) Introduction This AMC provides Guidance Material and Acceptable Means of Compliance for showing compliance with CS-E 780. 39. ## [CS-E 790 Ingestion of Rain and Hail](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-790-ingestion-of-rain-and-hail) All Engines. The ingestion of large hailstones (0.8 to 0.9 specific gravity) at the maximum true airspeed, for altitudes up to 4 500 metres, associated… 40. ## [AMC E 790 Rain and Hail Ingestion](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-790-rain-and-hail-ingestion) For the purposes of interpreting the words ‘unacceptable mechanical damage’ and ‘unacceptable power or thrust loss' in CS-E 790(a)(1), (a)(2), (b) and… 41. ## [AMC E 790(a)(1) Rain and Hail Ingestion Certification for Design Changes and Derivative Engines – Turbine Engine Power/Thrust Loss and Instability in Extreme Conditions of Rain and Hail](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-790-a-1-rain-and-hail-ingestion-certification-for-design-changes-and) CS-E 790(a)(1) allows, as an alternative to conducting a full Engine test, the certification of design changes or derivative Engines based on alternative… 42. ## [AMC E 790(a)(2) Rain and Hail Ingestion – Turbine Engine Power/ Thrust Loss and Instability in Extreme Conditions of Rain and Hail](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-790-a-2-rain-and-hail-ingestion-turbine-engine-power-thrust-loss-and) Definitions The following terms are defined for the purpose of this AMC: 43. ## [Appendix A Certification Standard Atmospheric Concentrations of Rain and Hail](https://avioverse.aero/regulations/easa/cs-e/subpart-e/appendix-a) Figure A1, Table A1, Table A2, Table A3 and Table A4 in this Appendix A specify the atmospheric concentrations and size distributions of rain and hail… 44. ## [CS-E 800 Bird Strike and Ingestion](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-800-bird-strike-and-ingestion) (See AMC E 800) (a) Objective. To demonstrate that the Engine will respond in a safe manner following specified encounters with birds, as part of the… 45. ## [AMC E 800 Bird Strike and Ingestion](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-800-bird-strike-and-ingestion) Ingestion tests (a) Single large bird (i) The applicant is required to provide an analysis substantiating the definition of the 'most critical exposed… 46. ## [CS-E 810 Compressor and Turbine Blade Failure](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-810-compressor-and-turbine-blade-failure) (See AMC E 810) (a) It must be demonstrated that any single compressor or turbine blade will be radially contained by the Engine after Failure and that… 47. ## [AMC E 810 Compressor and Turbine Blade Failure](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-810-compressor-and-turbine-blade-failure) ED Decision 20187/014/R (1) General (a) Compliance with the specifications of CS-E 810(a) may be shown in accordance with either (i), (ii) or (iii) - (i)… 48. ## [CS-E 820 Over-torque Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-820-over-torque-test) If approval of a Maximum Engine Over-torque for inadvertent occurrences is sought for an Engine incorporating a free power turbine, compliance with this… 49. ## [AMC E 820(a)(2) Over-torque Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-820-a-2-over-torque-test) In order to comply with CS-E 820(a)(2), it should be shown that an over-torque event does not compromise the ability of the Engine to reach its Rated… 50. ## [CS-E 830 Maximum Engine Over-speed](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-830-maximum-engine-over-speed) If approval of a Maximum Engine Over-speed for inadvertent occurrences is sought for a rotating system of the Engine, a test must be undertaken on a… 51. ## [AMC E 830(c) Maximum Engine Over-speed](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-830-c-maximum-engine-over-speed) In order to comply with CS-E 830(c), it should be shown that an over-speed event does not compromise the ability of the Engine to reach its Rated… 52. ## [CS-E 840 Rotor Integrity](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-840-rotor-integrity) (See AMC E 840) (a) For each fan, compressor, and turbine rotor, it must be established by test, analysis, or combination thereof, that a rotor which has… 53. ## [AMC E 840 Rotor Integrity](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-840-rotor-integrity) Definitions The following terms are defined for the purposes of interpreting CS-E 840 and this AMC. 54. ## [CS-E 850 Compressor, Fan and Turbine Shafts](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-850-compressor-fan-and-turbine-shafts) (See AMC E 850) (a) Objectives. It must be demonstrated that Failures of the shaft systems will not result in Hazardous Engine Effects, except as… 55. ## [AMC E 850 Compressor, Fan and Turbine Shafts](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-850-compressor-fan-and-turbine-shafts) General (a) A shaft is the system that transmits torque between the disc driving flange or the shaft attachment member of the system that produces power… 56. ## [CS-E 860 Turbine Rotor Over-temperature](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-860-turbine-rotor-over-temperature) The most critical temperature conditions which the turbine rotor(s) can attain in the event of Failures of the cooling air supply must be established by… 57. ## [CS-E 870 Exhaust Gas Over-temperature Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-870-exhaust-gas-over-temperature-test) General (1) Where the Applicant wishes to establish a Maximum Exhaust Gas Over-temperature limit for inadvertent occurrences, compliance must be shown… 58. ## [AMC E 870(a)(3) Exhaust Gas Over-temperature Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-870-a-3-exhaust-gas-over-temperature-test) In order to comply with CS-E 870(a)(3), it should be shown that an over-temperature event does not compromise the ability of the Engine to reach its… 59. ## [CS-E 880 Tests with Refrigerant Injection for Take-Off and/or 2½-Minute OEI Power](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-880-tests-with-refrigerant-injection-for-take-off-and-or-21-2-minute-oei) Engines for Rotorcraft. The variation of the tests prescribed in this subpart E when using refrigerant injection must be agreed in consultation with the… 60. ## [CS-E 890 Thrust Reverser Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-890-thrust-reverser-tests) (See AMC E 890) (a) Applicability. CS-E 890 is applicable to thrust reversers intended to be installed on turbine Engines. 61. ## [AMC E 890 Thrust Reverser Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-890-thrust-reverser-tests) Interpretation of CS-E 890(g): In cases where the Engine test of CS-E 740 cannot be run with the standard thrust reverser, for example because it is not… 62. ## [CS-E 900 Propeller Parking Brake](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-900-propeller-parking-brake) If a Propeller parking brake is provided it must be operated 100 times during the endurance test. 63. ## [CS-E 910 Relighting In Flight](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-910-relighting-in-flight) The Engine constructor must recommend an envelope of conditions for Engine relighting in flight, and must substantiate it by appropriate tests or other… 64. ## [AMC E 910 Relighting In Flight](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-910-relighting-in-flight) AMC 25.903(e)(2) contains guidance that can be used to establish the objectives of the demonstration of compliance of the Engine with CS-E 910. 65. ## [CS-E 920 Over-temperature Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-920-over-temperature-test) (See AMC E 920) (a) Each Engine must run for 5 minutes at maximum permissible rotational speed (rpm) with the turbine entry gas temperature at least 42… 66. ## [AMC E 920 Over-temperature test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/amc-e-920-over-temperature-test) To establish a datum turbine entry gas temperature, when this may vary at a fixed gas temperature operating limit dependent upon the deterioration… 67. ## [CS-E 930 Initial Maintenance Programme Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-930-initial-maintenance-programme-test) (See AMC E 930) A test must be performed with an Engine that adequately conforms to the type design to substantiate the initial maintenance programme… [AMC E 930 Initial Maintenance Programme Test](https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-930-initial-maintenance-programme-test#amc-e-930-initial-maintenance-programme-test) Consolidated from the EASA Easy Access Rules (revision 7 Dec 2023, extracted 13 Oct 2026) for convenience. 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