SUBPART D – TURBINE ENGINES: DESIGN AND CONSTRUCTION
Engines (CS-E) · CS-E
CS-E 500 Functioning
(See AMC E 500) (a) The Engine must be free from dangerous surge and instability throughout its operating range of ambient and running conditions within…
AMC E 500 Functioning - Control of Engines (Turbine Engines for Aeroplanes)
It is normally acceptable that the control of Engines within their limitations may be achieved by manual, as opposed to automatic, means provided that…
CS-E 510 Safety Analysis
(See AMC E 510) (a) (1) An analysis of the Engine, including the control system, must be carried out in order to assess the likely consequence of all…
AMC E 510 Safety analysis
Introduction. Compliance with CS-E 510 requires a safety analysis which should be substantiated, when necessary, by appropriate testing and/or comparable…
CS-E 515 Engine Critical Parts
(See AMC E 515) The integrity of the Engine Critical Parts identified under CS-E 510 must be established by:
AMC E 515 Engine Critical Parts
Introduction Because the Failure of an Engine Critical Part is likely to result in a Hazardous Engine Effect, it is necessary to take precautions to…
CS-E 520 Strength
The major rotating components of the Engine must have adequate strength to withstand both the thermal and dynamic conditions of normal operation and any…
AMC E 520(a) Strength - High Cycle Fatigue
In order to minimise the adverse consequences of Failures due to unpredicted high cycle fatigue it is recommended that, normally, the relative fatigue…
AMC E 520(c)(1) Strength - Shedding of Blades
In order to reduce the risk of a single blade Failure leading to a multiple blade Failure and possible non-containment, particular attention should be…
AMC E 520(c)(2) Engine Model Validation
Validated data specifically for blade loss analysis typically include:
AMC E 520(d) Strength – Local Failures
Local Failures of the Engine casing may include localised cracking.
CS-E 525 Continued Rotation
(see AMC E 525) If any of the Engine’s main rotating systems will continue to rotate after the Engine is shutdown for any reason while in flight, and…
AMC E 525 Continued rotation
Continued rotation can be either due to windmilling or due to mechanical effects such as clutch drag in the case of a multi-engined rotorcraft.
CS-E 540 Strike and Ingestion of Foreign Matter
(See AMC E 540) (a) The Engine must be designed so that the strike and ingestion of foreign matter that is likely to affect only one Engine in any one…
AMC E 540 Strike and ingestion of foreign matter
When complying with CS-E 540(a), the substantiation of the strike and ingestion effects of foreign objects such as cleaning cloths, hand tools, rivets…
CS-E 560 Fuel System
(See AMC E 560) (a) (1) Each fuel specification to be approved, including any additive, and the associated limitations in flow, temperature and pressure…
AMC E 560 Fuel System
More than one type of fuel may be allowed: CS-E 560(a) applies to each type and covers additives in the fuel (for example, fuel system icing inhibitor).
CS-E 570 Oil System
(See AMC E 570) (a) (1) The design of the oil system must be such as to ensure its proper functioning under all intended flight attitudes, installation…
AMC E 570 Oil system
Each filter or strainer requiring regular servicing should be accessible for draining and cleaning or replacement.
CS-E 580 Air Systems
Where bleed air is used to cool or to pressurise areas of the Engine, the functions of which could be detrimentally affected by the ingress of foreign…
CS-E 590 Starter Systems
Where the starter is declared as part of the Engine, its design, and that of its associated drive mechanism, must be such that over-speeding of the…
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