[PDF] CS-23 Amdt 5 29?/03?/2017 Amendment 5.

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European Union Aviation Safety Agency

Certification Specifications

and

Acceptable Means of Compliance

for

Engines

CS-E

Amendment 5

13 December 20181

1 For the date of entry into force of this Amendment, please refer to Decision 2018/014/R in the Official Publication of

EASA. CS-E C-1

CONTENTS (General layout)

PREAMBLE

CS-E 10 Applicability

CS-E 15 Terminology

CS-E 20 Engine Configuration and Interfaces

CS-E 25 Instructions for Continued Airworthiness

CS-E 30 Assumptions

CS-E 40 Ratings

CS-E 50 Engine Control System

CS-E 60 Provision for Instruments

CS-E 70 Materials and Manufacturing Methods

CS-E 80 Equipment

CS-E 90 Prevention of Corrosion and Deterioration

CS-E 100 Strength

CS-E 120 Identification

CS-E 130 Fire Protection

CS-E 135 Electrical Bonding

CS-E 170 Engine systems and component verification

CS-E 180 Propeller Functioning Tests

CS-E 190 Engines for Aerobatic Use

CS-E 210 Failure Analysis

CS-E 230 De-Icing and Anti-Icing Precautions

CS-E 240 Ignition

CS-E 250 Fuel System

CS-E 260 Engine Cooling System

CS-E 270 Lubrication System

CS-E 290 Hand Turning

CS-E C-2

CS-E 300 Conditions Applicable to All Tests

CS-E 320 Performance Correction

CS-E 340 Vibration Tests

CS-E 350 Calibration Tests

CS-E 360 Detonation Tests

CS-E 370 Starting Tests

CS-E 380 Low-Temperature Starting Tests

CS-E 390 Acceleration Tests

CS-E 400 Over-speed Tests

CS-E 430 Water Spray Tests

CS-E 440 Endurance Tests

CS-E 450 Ignition Tests

CS-E 460 Backfire Tests

CS-E 470 Contaminated Fuel

CS-E 500 Functioning

CS-E 510 Safety Analysis

CS-E 515 Engine Critical Parts

CS-E 520 Strength

CS-E 525 Continued Rotation

CS-E 540 Strike and Ingestion of Foreign Matter

CS-E 560 Fuel System

CS-E 570 Oil System

CS-E 580 Air Systems

CS-E 590 Starter Systems

CS-E 620 Performance Correction

CS-E 640 Pressure Loads

CS-E 650 Vibration Surveys

CS-E 660 Fuel Pressure and Temperature

CS-E 670 Contaminated Fuel

CS-E 680 Inclination and Gyroscopic Load Effects

CS-E 690 Engine Bleed

CS-E 700 Excess Operating Conditions

CS-E C-3

CS-E 710 Rotor Locking Tests

CS-E 720 Continuous Ignition

CS-E 730 Engine Calibration Tests

CS-E 740 Endurance Tests

CS-E 745 Engine Acceleration

CS-E 750 Starting Tests

CS-E 770 Low-Temperature Starting Tests

CS-E 780 Tests in Ice-Forming Conditions

CS-E 790 Ingestion of Rain and Hail

CS-E 800 Bird Strike and Ingestion

CS-E 810 Compressor and Turbine Blade Failure

CS-E 820 Over-torque Test

CS-E 830 Maximum Engine Over-speed

CS-E 840 Rotor Integrity

CS-E 850 Compressor, Fan and Turbine Shafts

CS-E 860 Turbine Rotor Over-temperature

CS-E 870 Exhaust Gas Over-temperature Test

CS-E 880 Tests with Refrigerant Injection for Take-Off and/or 2 ½-Minute OEI Power

CS-E 890 Thrust Reverser Tests

CS-E 900 Propeller Parking Brake

CS-E 910 Relighting in Flight

CS-E 920 Over-temperature Test

CS-E 1000 General

CS-E 1010 Fuel Venting

CS-E 1020 Engine Emissions

CS-E 1030 Time-Limited Dispatch

CS-E 1040 ETOPS

CS-E 1050 Exposure to Volcanic Cloud Hazards

APPENDICES

Appendix A Certification Standard Atmospheric Concentrations for Rain and Hail

AMC E 10(b) Thrust Reversers

CS-E C-4

AMC E 20 Engine Configuration and Interfaces

AMC E 20(f) Power Assurance Data for Engines with One or More OEI Power

Ratings

AMC E 25 Instructions for Continued Airworthiness

AMC E 30 Assumptions

AMC E 40 Ratings

AMC E 40(b)(3) 30-Second OEI and 2-Minute OEI Ratings

AMC E 40(d) Operating Limitations

AMC E 50 Engine Control System

AMC E 50(e) Rotor Integrity

AMC E 60 Provision for Instruments

AMC E 60(d) Provision for Instruments

AMC E 70 Castings, Forgings, Welded Structures and Welded Components

AMC E 80 Equipment

AMC E 130 Fire Protection

AMC E 135 Electrical Bonding

AMC E 170 Engine Systems and Component Verification

AMC E 180 Propeller Functioning Tests

AMC E 210 Failure Analysis

AMC E 320 Performance Correction

AMC E 340 Vibration Tests

AMC E 350 Calibration Tests

AMC E 380 Low-Temperature Starting Tests

AMC E 470 Contaminated Fuel

AMC E 510 Safety Analysis

AMC E 515 Engine Critical Parts

CS-E C-5

AMC E 520(c)(2) Engine Model Validation

AMC E 525 Continued Rotation

AMC E 540 Strike and Ingestion of Foreign Matter

AMC E 560 Fuel System

AMC E 570 Oil System

AMC E 620 Performance: Formulae

AMC E 640 Static Pressure and Fatigue Tests

AMC E 650 Vibration Surveys

AMC E 660 Fuel Pump Tests (Turbine Engines for Aeroplanes)

AMC E 670 Contaminated Fuel Testing

AMC E 680 Inclination and Gyroscopic Load Effects

AMC E 690 Engine Bleed

AMC E 700 Excess Operating Conditions (Turbine Engines for Aeroplanes)

AMC E 710 Rotor Locking Tests

AMC E 720(a) Continuous Ignition

AMC E 730 Calibration Tests

AMC E 740(c)(3) Endurance Tests

AMC E 740(f)(1) Multi-Spool Engines

AMC E 745 Engine Acceleration

AMC E 750 (b) Starting Tests

AMC E 770 Low-Temperature Starting Tests

AMC E 780 Tests in Ice-Forming Conditions

AMC E 790 Rain and Hail Ingestion

AMC E 790(a)(1) Rain and Hail Ingestion Certification for Design Changes and Instability in Extreme Conditions of Rain and Hail Instability in Extreme Conditions of Rain and Hail

AMC E 800 Bird Strike and Ingestion

AMC E 810 Compressor and Turbine Blade Failure

AMC E 820(a)(2) Over-torque Test

AMC E 830(c) Maximum Engine Over-speed

AMC E 840 Rotor Integrity

CS-E C-6

AMC E 850 Compressor, Fan and Turbine Shafts

AMC E 870(a)(3) Exhaust Gas Over-temperature Test

AMC E 890 Thrust Reverser Tests

AMC E 910 Relighting In Flight

AMC E 920 Over-temperature Test

AMC E 1020 Engine Emissions

AMC E 1030 Time-Limited Dispatch

AMC E 1050 Exposure to Volcanic Cloud Hazards

CS-E P-1

PREAMBLE

CS-E Amendment 5

Effective: see Decision 2018/014/R

The following is a list of paragraphs that are affected by this Amendment. Editorial corrections made to the entire CS-E Amendment 5.

CONTENTS (General layout)

Book 1

BOOK 2

CS-E P-2

CS-E Amendment 4

Effective: see Decision 2015/009/R

The following is a list of paragraphs affected by this Amendment.

CONTENTS (General layout)

SUBPART D

Book 1

Subpart E

SUBPART F

BOOK 2

SUBPART A

SUBPART E

SUBPART F

CS-E P-3

CS-E Amendment 3

Effective: 23/12/2010

The following is a list of paragraphs affected by this Amendment.

BOOK 1

SUBPART F

CS-E Amendment 2

Effective: 18/12/2009

The following is a list of paragraphs affected by this Amendment.

BOOK 1

SUBPART A

SUBPART D

BOOK 2

SUBPART A

SUBPART D

CS-E P-4

CS-E Amendment 1

Effective: 10/12/2007

The following is a list of paragraphs affected by this Amendment.

CONTENTS (General layout) Amended (NPA 3/2005)

BOOK 1

SUBPART A

SUBPART B

SUBPART C

SUBPART D

CS-E P-5

SUBPART E

SUBPART F

BOOK 2

CS-E P-6 CS-E P-7 CS-E

EASA Certification Specifications

for

Engines

CS-E

Book 1

Certification specifications

CS-E BOOK 1

1-A-1

CS-E 10 Applicability

(a) This CS-E contains airworthiness specifications for the issue of type certificates, and changes to those certificates, for Engines, in accordance with Part 21. (b) CS-E contains the specifications for the approval for use of the Engine with a thrust reverser, if fitted. If compliance is shown, the specific thrust reverser approved for use will be noted in the Engine certification documentation. Otherwise, the documentation will be endorsed to indicate that the use of a thrust reverser is prohibited (see AMC E 10(b)). (c) The specifications of Subparts A, B and C apply to Piston Engines. Any necessary variations of the specifications of Subparts B and C for Piston Engines intended for use in Rotorcraft will be decided in accordance with 21A.16. (d) The specifications of Subparts A, D, E and F apply to Turbine Engines. [Amdt No: E/1] [Amdt No: E/5]

CS-E 15 Terminology

(a) 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. Where used in CS-E, the terms defined in this paragraph and in CS-Definitions are identified by initial capital letters. (b) All Engines Extremely Remote: means unlikely to occur when considering the total operational life of a number of aircraft of the type in which the Engine is installed, but nevertheless, has to be regarded as being possible. Where numerical values are used this may normally be interpreted as a probability in the range 10-7 to 10-9 per Engine flight hour. Reasonably Probable: means unlikely to occur often during the operation of each aircraft of the type but which may occur several times during the total operational life of each aircraft of the types in which the Engine may be installed. Where numerical values are used this may normally be interpreted as a probability in the range 10-3 to 10-5 per

Engine flight hour.

Remote: means unlikely to occur to each aircraft during its total operational life but may occur several times when considering the total operational life of a number of aircraft of the type in which the Engine may be installed. When numerical values are used, this may normally be interpreted as a probability in the range 10-5 to 10-7 per

Engine flight hour.

(c) Turbine Engines Hazardous Engine Effect: means an effect identified as such under CS-E 510.

CS-E BOOK 1

1-A-2 Major Engine Effect: means an effect identified as such under CS-E 510. Minor Engine Effect: means an effect identified as such under CS-E 510. (d) For piston Engines Boost Pressure: means the power setting measured relative to standard sea-level atmospheric pressure. Charge Cooling: means the percentage degree of charge cooling, quantitatively expressed as: ((t2 - t3) / (t2 - t1)) × 100 where: t1 is the temperature of the air entering the charge cooler coolant radiator in the powerplant, t2 is the temperature of the charge without cooling, and t3 is the temperature of the charge with cooling. Critical Altitude: means the maximum attitude at which, in standard atmosphere, it is possible to maintain, at a specified rotational speed without ram, a specified power or a specified manifold pressure. Unless otherwise stated, the critical altitude is the maximum altitude at which it is possible to maintain, without ram, at the maximum continuous rotational speed, one of the following: a. The maximum continuous power, in the case of engines for which this power rating is the same at sea level and at the rated altitude. b. The maximum continuous rated manifold pressure, in the case of engines the maximum continuous power of which is governed by a constant manifold pressure. Manifold Pressure: means the absolute static pressure measured at the appropriate point in the induction system.

Maximum Best Economy

Cruising Power Conditions: means the crankshaft rotational speed, Engine manifold pressure and any other parameters recommended in the Engine manuals as appropriate for use with economical- cruising mixture strength.

Maximum Recommended

Cruising Power Conditions: means the crankshaft rotational speed, Engine manifold pressure and any other parameters recommended in the Engine manuals as appropriate for cruising operation. (e) Terms associated with Engine Critical Parts Approved Life: means the mandatory replacement life of a part which is approved by the Agency. Attributes: means inherent characteristics of a finished part that determine its capability.

CS-E BOOK 1

1-A-3 Damage Tolerance: means an element of the life management process that recognises the potential existence of component imperfections as the result of inherent material structure, material processing, component design, manufacturing or usage and addresses this situation through the incorporation of fracture resistant design, fracture mechanics, process control, and non-destructive inspection. Engine Critical Part: means a part that relies upon meeting prescribed integrity specifications of CS-E 515 to avoid its Primary Failure, which is likely to result in a Hazardous Engine

Effect.

Engine Flight Cycle: means the flight profile, or combination of profiles, upon which the Approved Life is based. Engineering Plan: means a compilation of the assumptions, technical data and actions required to establish and to maintain the life capability of an Engine Critical Part. The Engineering Plan is established and executed as part of the pre- and post- certification activities. Manufacturing Plan: means a compilation of the part specific manufacturing process constraints, which must be included in the manufacturing definition (drawings, procedures, specifications, etc.) of the Engine Critical Part to ensure that it meets the design intent as defined by the

Engineering Plan.

Primary Failure: means a Failure of a part which is not the result of the prior Failure of another part or system. Service Management Plan: means a compilation of the processes for in-service maintenance and repair to ensure that an Engine Critical Part achieves the design intent as defined by the

Engineering Plan.

[Amdt No: E/1] [Amdt No: E/2] [Amdt No: E/5]

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 Engine, must be established. (b) The aircraft certification specification which is assumed to be applicable to the intended installation of the Engine must be identified under CS-E 30. (c) The aircraft parts and equipment that may be mounted on, or driven by, the Engine, which are not part of the declared Engine configuration and therefore are not covered by the

Engine Type Certificate must be identified.

(d) Manuals must be provided containing instructions for installing and operating the Engine. These instructions must contain a definition of the physical and functional interfaces with the

CS-E BOOK 1

1-A-4 aircraft and aircraft equipment. They must also include a description of the Primary and all Alternate Modes, and any Back-up System, together with any associated limitations, of the Engine Control System and its interface with the aircraft systems, including the Propeller when applicable.quotesdbs_dbs11.pdfusesText_17

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