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 code 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 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.

(e)Engine performance data, compatible with the Engine acceptance and operating limitations, must be provided for aircraft certification performance, handling and stressing purposes. The data must be such that the power/thrust of a ‘minimum’ and a ‘maximum’ Engine can be derived and must include means of determining the effects on performance of variations of Engine bleed and power off-take, forward speed, ambient pressure, temperature and humidity.

(f)For Engines having one or more OEI Ratings, data must be provided on Engine performance characteristics and variability to enable the aircraft manufacturer to establish power assurance procedures. (See AMC E 20(f))

[Amdt No: E/1]

[Amdt No: E/5]