SUBPART E – TURBINE ENGINES: TYPE SUBSTANTIATION
Engines (CS-E) · CS-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.
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.
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…
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…
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…
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.
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…
AMC E 650 Vibration Surveys
Definitions. The following are defined for the purpose of this AMC:
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.
AMC E 660 Fuel Pump Tests (Turbine Engines for Aeroplanes)
When testing equipment susceptible to cavitation erosion (e.g.
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…
AMC E 670 Contaminated Fuel Testing
Solid Contaminants (a) A contaminant with the characteristics detailed in the following table is acceptable.
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…
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…
CS-E 690 Engine Bleed
(See AMC E 690) (a) For an Engine having bleed(s) for aircraft and/or Engine uses, the standard Engine endurance test schedule of CS-E 740 must be varied…
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…
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…
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…
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…
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.
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)…
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…
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, thrust or power calibration…
AMC E 730 Calibration Tests
The parameters used for the calibration curves are those appropriate to, and compatible with, the Engine’s design.
CS-E 740 Endurance Tests
ED Decision 208/014/R (a) The specifications of this CS-E 740 must be varied and supplemented as necessary to comply with CS-E 690(a), CS-E 750 and CS-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:
AMC E 740(c)(3) Endurance tests
Two procedures for running the tests required under CS-E 740(c)(3) are acceptable:
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…
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…
AMC E 740(h)(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…
CS-E 745 Engine Acceleration
(See AMC E 745) (a) It must be demonstrated, on a test bed, that:
AMC E 745 Engine Acceleration
Compliance with CS-E 745 may be demonstrated during tests performed to meet other sections of CS-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.
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…
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…
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.
CS-E 780 Icing Conditions
(See AMC E 780) (a) It must be established by tests, unless alternative appropriate evidence is available, that the Engine will function satisfactorily…
AMC E 780 Icing Conditions
Introduction This AMC provides Guidance Material and Acceptable Means of Compliance for showing compliance with CS-E 780.
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…
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…
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
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…
AMC E 790(a)(2) Rain and Hail Ingestion – Turbine Engine Power/ Thrust Loss and Instability in Extreme Conditions of Rain and Hail
Definitions The following terms are defined for the purpose of this AMC:
Appendix A Certification Standard Atmospheric Concentrations of Rain and Hail
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…
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…
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…
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 contained after Failure and that no Hazardous Engine…
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)…
CS-E 820 Over-torque Test
If approval of a Maximum Engine Over-torque is sought for an Engine incorporating a free power turbine, compliance with this paragraph must be…
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…
CS-E 830 Maximum Engine Over-speed
If approval of a Maximum Engine Over-speed is sought for a rotating system of the Engine, a test must be undertaken on a complete Engine.
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…
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…
AMC E 840 Rotor Integrity
Definitions The following terms are defined for the purposes of interpreting CS-E 840 and this AMC.
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…
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…
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…
CS-E 870 Exhaust Gas Over-temperature Test
General (1) Where the Applicant wishes to establish a Maximum Exhaust Gas Over-temperature limit compliance must be shown with this paragraph CS-E 870.
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…
CS-E 880 Tests with Refrigerant Injection for Take-Off and/or 2½-Minute OEI Power
Engines for Rotorcraft. The variation of the tests prescribed in this subpart E when using refrigerant injection must be agreed in consultation with the…
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.
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…
CS-E 900 Propeller Parking Brake
If a Propeller parking brake is provided it must be operated 100 times during the endurance test.
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…
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.
CS-E 920 Over-temperature Test
(See AMC E 920) For Engines with 30-Second and 2-Minute OEI Power ratings, the Engine must be run for a period of 4 minutes at the maximum power-on rotor…
AMC E 920 Over-temperature test
For the purpose of the test of CS-E 920, "Maximum power-on rpm" is normally the steady state rotor speed associated with the 30-Second OEI Power rating.
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