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

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

AMC E 700 Excess Operating Conditions (Turbine Engines for Aeroplanes) ED Decision 2007/015/R (1) 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 operation at VMO under the most critical ambient pressure and temperature conditions, with Maximum Continuous Power and/or Thrust selected. The duration of the test should be related to the likelihood of the conditions occurring and the frequency of the occurrence in respect of a representative type of aeroplane. If limitations are declared and provision made for the necessary instrumentation, the test conditions may be modified accordingly. On conclusion of the test, the Engine should be subjected to a strip examination and should not reveal features that could lead to a significant increase in the risk of Engine Failure. (2) Case at VD. The Engine should be run for 5 minutes (comprising five 1 minute runs or fewer longer runs of equal total duration) at the excess pressures and thrusts, which would result from operation at VD under the most critical ambient pressure and temperature conditions, with Maximum Continuous Power and/or Thrust selected, followed by the demonstration of ability of the Engine to complete a flight in which such circumstances have occurred. This latter demonstration may consist of running the Engine at typical cruising conditions for a period equal to the maximum likely flight time following such an incident on a representative type of aeroplane. The value should be established in consultation with the Agency. (3) Case of 'Throttle Slam'. The Engine should be rapidly accelerated from minimum flight idle conditions in simulation of throttle slam (i.e. opening the throttle as rapidly as is physically possible) and then run for two minutes to cover the excess conditions (e.g. rpm, pressure, thrust, temperature), which result from operating the Engine with the power control lever in the maximum forward position under the most critical ambient conditions likely to exist within the range of aerodrome altitudes for which performance is scheduled. If desired, the 2 minutes test may be made up of separate tests, each of not less than one-minute duration. At the end of the test the condition of the Engine should be such as to enable it to complete a flight in which such circumstances have occurred. This may be shown by demonstrating that the Engine will run satisfactorily at typical cruising conditions for a continuous period of 30 minutes (see also [AMC E 500](#_DxCrossRefBm1371447721) paragraph 3). (4) When exceedence of an Engine operating limitation has occurred during the bird tests of [CS-E 800(c)](#_DxCrossRefBm1371447598) or (d), it should be demonstrated in compliance with [CS-E 700](#_DxCrossRefBm1371447774) that the value of the exceeded parameter which was reached during the testing has been adequately validated by other tests of CS-E or by specific additional test if needed. The maintenance actions associated with such exceedences for a similar in-service event should also be adequately validated and documented in the appropriate manuals. Compliance with [CS-E 700](#_DxCrossRefBm1371447774) might include consideration either of a change in the finally certified limit so that the value achieved during the test would no longer be an exceedence, or of an approval of a transient under [CS-E 820](#_DxCrossRefBm1371447645), [CS-E 830](#_DxCrossRefBm1371447644) or [CS-E 870](#_DxCrossRefBm1371447643) as appropriate. [Amdt. No.: E/1]