--- title: "SUBPART A – GENERAL — CS-E — rule index · Avioverse" description: "SUBPART A – GENERAL (46 paragraphs), CS-E. This CS-E contains airworthiness specifications for the issue of type certificates, and changes to those…" url: "https://avioverse.aero/regulations/easa/cs-e/subpart-a" --- # SUBPART A – GENERAL Engines (CS-E) · CS-E 1. ## [AMC General](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-general) In addition to the acceptable means of compliance in Book 2 of these Certification Specifications, AMC-20 may also provide acceptable means of compliance… 2. ## [CS-E 10 Applicability](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-10-applicability) This CS-E contains airworthiness specifications for the issue of type certificates, and changes to those certificates, for Engines, in accordance with… 3. ## [AMC E 10(b) Thrust Reversers](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-10-b-thrust-reversers) If a thrust reverser is declared as being part of the Engine type design under CS-E 20(a), it should comply with all appropriate CS-E specifications and… 4. ## [CS-E 15 Terminology](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-15-terminology) The terminology of this CS-E 15 must be used in conjunction with the issue of CS-Definitions current at the date of issue of this CS-E. 5. ## [CS-E 20 Engine Configuration and Interfaces](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-20-engine-configuration-and-interfaces) (See AMC E 20) (a) The list of all the parts and equipment, including references to the relevant drawings, which defines the proposed type design of the… 6. ## [AMC E 20 Engine Configuration and Interfaces](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-20-engine-configuration-and-interfaces) The components and equipment listed in the Engine type design (see CS-E 20(a)) should include those items necessary for the satisfactory functioning and… 7. ## [AMC E 20(f) Power Assurance Data for Engines with One or more OEI Power Ratings](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-20-f-power-assurance-data-for-engines-with-one-or-more-oei-power-ratings) For Engines having one or more OEI ratings, the applicant should provide in the instructions for installation the necessary Engine data to support the… 8. ## [CS-E 25 Instructions for Continued Airworthiness](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-25-instructions-for-continued-airworthiness) (See AMC E 25) (a) Manual(s) must be established containing instructions for continued airworthiness of the Engine. 9. ## [AMC E 25 Instructions for continued airworthiness](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-25-instructions-for-continued-airworthiness) The maintenance actions are determined through certification testing, including, where applicable, endurance tests, initial maintenance programme test… 10. ## [CS-E 30 Assumptions](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-30-assumptions) (See AMC E 30) (a) In the course of establishing compliance with CS-E certain assumptions have to be made concerning the conditions that may be imposed… 11. ## [AMC E 30 Assumptions](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-30-assumptions) The details required by CS-E 30 concerning assumptions should normally include information on, at least, the items listed in Table 1. 12. ## [CS-E 40 Ratings](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-40-ratings) (See AMC E 40) (a) Power ratings must be established for Take-off Power and/or Thrust and for Maximum Continuous Power and/or Thrust, for all Engines. 13. ## [AMC E 40 Ratings](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-40-ratings) The thrust and / or power ratings to be approved should be adequately justified by the applicant, using as appropriate the results of the calibration… 14. ## [AMC E 40(b)(3) and (b)(4) 30-Second OEI, 2-Minute OEI and 30-minute Power Ratings](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-40-b-3-and-b-4-30-second-oei-2-minute-oei-and-30-minute-power-ratings) The 30-Second and 2-Minute OEI Power ratings are two separate ratings. 15. ## [AMC E 40(d) Operating Limitations](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-40-d-operating-limitations) The Operating limitations established under CS-E 40(d) should normally include those items listed below. 16. ## [CS-E 50 Engine Control System](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-50-engine-control-system) (See AMC E 50, AMC 20-1, AMC 20-3, AMC 20-115, AMC 20-152, AMC 20-189, AMC 20-193) (a) Engine Control System Operation. [AMC to CS-E 50(l) Information system security protection](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-50-engine-control-system#amc-to-cs-e-50-l) 17. ## [AMC E 50 Engine Control System](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-50-engine-control-system) Applicability CS-E 50 is applicable to all types of Engine Control Systems. 18. ## [AMC E 50(e) Rotor integrity](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-50-e-rotor-integrity) The Engine control devices, systems and instruments referred to in CS-E 50(e) are usually provided in modern engines by over-speed protection and/or… 19. ## [AMC E 50(j) Controls - Engines having a 30-Second OEI Power Rating](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-50-j-controls-engines-having-a-30-second-oei-power-rating) The 30-Second OEI rating is intended to provide a rotorcraft with a power reserve in the event of one Engine becoming inoperative. 20. ## [CS-E 60 Provision for Instruments](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-60-provision-for-instruments) (See AMC E 60) (a) Provision must be made for the installation of instrumentation necessary to ensure operation in compliance with the Engine operating… 21. ## [AMC E 60 Provision for instruments](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-60-provision-for-instruments) Under the specifications of CS-E 60(a), the Engine manufacturer should define the instrumentation which is necessary for Engine operation within its… 22. ## [AMC E 60(d) Provision for instruments](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-60-d-provision-for-instruments) For the purpose of complying with CS-E 60(d), the 30-Second OEI power level is considered to be used whenever one or more of the operating limitations… 23. ## [CS-E 70 Materials and Manufacturing Methods](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-70-materials-and-manufacturing-methods) (See AMC E 70) (a) The suitability and durability of materials used in the Engine must be established on the basis of experience or tests. 24. ## [AMC E 70 Castings, Forgings, Welded Structures and Welded Components](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-70-castings-forgings-welded-structures-and-welded-components) Castings The means of maintaining the required quality of all castings should be established by such methods as analysis for correct chemical… 25. ## [CS-E 80 Equipment](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-80-equipment) (See AMC E 80) (a) Equipment Drives and Mountings (1) Mountings and drives for all equipment installed on the Engine must be designed: 26. ## [AMC E 80 Equipment](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-80-equipment) The need for additional specifications in the equipment specifications should be determined when complying with CS-E 80 or be defined by the applicant on… 27. ## [CS-E 90 Prevention of Corrosion and Deterioration](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-90-prevention-of-corrosion-and-deterioration) Each Engine component and each item of equipment must be protected from corrosion and deterioration in an approved manner. 28. ## [CS-E 100 Strength](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-100-strength) The maximum stresses developed in the Engine must not exceed values conforming to those established by satisfactory practice for the material involved… 29. ## [CS-E 110 Drawings and Marking of Parts – Assembly of Parts](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-110-drawings-and-marking-of-parts-assembly-of-parts) The drawings for each Engine component and each item of equipment must give full particulars of the design and must indicate the materials used in terms… 30. ## [CS-E 120 Identification](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-120-identification) The Engine identification must comply with points 21.A.801(a) and (b), and point 21.A.805 of Part 21. 31. ## [CS-E 130 Fire Protection](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-130-fire-protection) (See AMC E 130) (a) The design and construction of the Engine and the materials used must minimise the probability of the occurrence and spread of fire… 32. ## [AMC E 130 Fire Protection](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-130-fire-protection) Definitions (a) Drain and Vent Systems: Components which are used to convey unused or unwanted quantities of flammable fluid or vapour away from the… 33. ## [CS-E 135 Electrical Bonding](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-135-electrical-bonding) (See AMC E 135) Any components, modules, equipment and accessories that are susceptible to or are potential sources of static discharges or currents from… 34. ## [AMC E 135 Electrical Bonding](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-135-electrical-bonding) Electrical bonding is a means to protect against the effects of electro-static discharges and currents from electrical Faults. 35. ## [CS-E 140 Tests - Engine Configuration](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-140-tests-engine-configuration) (See AMC E 140) (a) The configuration of the Engine or components or parts to be tested must be sufficiently representative of the type design for the… 36. ## [AMC E 140 Test - Engine configuration](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-140-test-engine-configuration) For turbine engines, if the power turbine accessory drives are not loaded, the equivalent power should be added as required by CS-E 140(d)(1) to the… 37. ## [CS-E 150 Tests - General Conduct of Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-150-tests-general-conduct-of-tests) The fuel and oil used for all tests must normally be chosen from those specified by the Applicant, but, where it may have relevance to the results of any… 38. ## [AMC E 150(a) Tests - General conduct of tests](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-150-a-tests-general-conduct-of-tests) For piston Engines, where the operating conditions of a test represent Maximum Continuous Power at altitude, a higher grade fuel or any other approved… 39. ## [CS-E 160 Tests - History](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-160-tests-history) In order to enable compliance with point 21.A.20(d)2 of Part 21, should a Failure of an Engine part occur during the certification tests, its cause must… 40. ## [CS-E 170 Engine Systems and Component Verification](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-170-engine-systems-and-component-verification) (See AMC E 170) For those systems or components which cannot be adequately substantiated by other tests of CS-E, additional tests or analyses must be… 41. ## [AMC E 170 Engine systems and component verification](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-170-engine-systems-and-component-verification) The intent of CS-E 170 is to define the additional tests or analysis which would be necessary for those systems or components which are not necessarily… 42. ## [CS-E 175 Propeller Blade Pitch Control System Components](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-175-propeller-blade-pitch-control-system-components) Each component of the Propeller blade pitch control system that is included in the Engine type design must comply with the following certification… 43. ## [CS-E 180 Propeller Functioning Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-180-propeller-functioning-tests) (See AMC E 180) (a) If approval of the Engine for use with a Variable Pitch Propeller is sought by the Applicant, a sufficient portion of the tests… 44. ## [AMC E 180 Propeller Functioning Tests](https://avioverse.aero/regulations/easa/cs-e/subpart-a/amc-e-180-propeller-functioning-tests) For Propeller approval the remaining tests of CS-P may be conducted on another Engine of the same type providing the same Propeller without further… 45. ## [CS-E 190 Engines for Aerobatic Use](https://avioverse.aero/regulations/easa/cs-e/subpart-a/cs-e-190-engines-for-aerobatic-use) Where approval is sought for an Engine intended for use in an aeroplane for which the Flight Manual will approve aerobatics or semi-aerobatic flight, the… Consolidated from the EASA Easy Access Rules (revision 7 Dec 2023, extracted 13 Oct 2026) for convenience. 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