CS-E 745 Engine Acceleration

• ED Decision 2007/015/R found in: CS-E Amdt 5 - Engines (Dec 2018)

CS-E 745 Engine Acceleration ED Decision 2007/015/R (See [AMC E 745](#_DxCrossRefBm1371447796)) (a) It must be demonstrated, on a test bed, that: (1) For aeroplane Engines, the power / thrust increases to rated Take-off when the power or thrust control lever is moved in not more than one second from the minimum flight idle position to the maximum position with the appropriate adverse combination of bleed air and power extraction to be permitted in the aeroplane, without over-temperature, surge, stall, or other detrimental factors occurring to the Engine. (2) For rotorcraft Engines, the power increases to rated Take-off when the power demand is increased from minimum test bed idle to rated Take-off in not more than one second with the appropriate adverse combination of bleed air and power extraction to be permitted in the aircraft, without over-temperature, surge, stall, or other detrimental factors occurring to the Engine. (3) For all Engines, an increase can be made from 15% of the rated Take-off Power or thrust, to 95% of the rated Take-off Power or thrust in a time not greater than 5 seconds. A longer time may be accepted if properly justified. This power or thrust response must occur from a stabilised static condition using only the bleed air and accessories loads necessary to run the Engine. (b) The minimum response time to 95% of the rated Take-off Power or thrust as a result of moving the power lever of aeroplane Engines in not more than one second, from minimum ground idle and from minimum flight idle positions or, for rotorcraft Engines, increasing the power demand in not more than one second from the minimum test bed idle condition, starting from a stabilised condition, must be measured under the following Engine load conditions. (1) No bleed air and power extraction for aircraft use. (2) Maximum allowable bleed air and power extraction for aircraft use. (3) An intermediate value for bleed air and power extraction representative of that which might be used as a maximum for aircraft during approach to a landing. (c) If testing facilities are not available to demonstrate the effects of power extraction required in CS-E 745(b)(2) and (3), this must be accomplished through appropriate analytical means. [Amdt No: E/1]