ED Decision 2003/18/RM
(a) The engine mount and its supporting structure must be designed for the effects of -
(1) A limit engine torque corresponding to take-off power and propeller speed acting simultaneously with 75% of the limit loads from flight condition A of CS-VLA 333(d);
(2) The limit engine torque as specified in CS-VLA 361(b) acting simultaneously with the limit loads from flight condition A of CS-VLA 333(d); and
(b) The limit engine torque to be considered under subparagraph (a)(2) of this paragraph must be obtained by multiplying the mean torque for maximum continuous power by a factor determined as follows:
(1) For four-stroke engines -
(i) 1·33 for engines with five or more cylinders,
(ii) 2, 3, 4 or 8, for engines with four, three, two or one cylinders, respectively.
(2) For two-stroke engines -
(i) 2 for engines with three or more cylinders,
(ii) 3 or 6, for engines with two or one cylinder respectively.
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