CS 25.1001 Fuel jettisoning system

ED Decision 2003/2/RM

(a)     A fuel jettisoning system must be installed on each aeroplane unless it is shown that the aeroplane meets the climb requirements of CS 25.119 and 25.121(d) at maximum take-off weight, less the actual or computed weight of fuel necessary for a 15-minute flight comprised of a take-off, go-around, and landing at the airport of departure with the aeroplane configuration, speed, power, and thrust the same as that used in meeting the applicable take-off, approach, and landing climb performance requirements of this CS-25.

(b)     If a fuel jettisoning system is required it must be capable of jettisoning enough fuel within 15 minutes, starting with the weight given in sub-paragraph (a) of this paragraph, to enable the aeroplane to meet the climb requirements of CS 25.119 and 25.121(d), assuming that the fuel is jettisoned under the conditions, except weight, found least favourable during the flight tests prescribed in sub-paragraph (c) of this paragraph.

(c)      Fuel jettisoning must be demonstrated beginning at maximum take-off weight with wingflaps and landing gear up and in –

(1)     A power-off glide at 1·3 V_SR1;

(2)     A climb at the one-engine inoperative best rate-of-climb speed, with the critical engine inoperative and the remaining engines at maximum continuous power; and

(3)     Level flight at 1·3 V_SR1, if the results of the tests in the condition specified in sub-paragraphs (c)(1) and (2) of this paragraph show that this condition could be critical.

(d)     During the flight tests prescribed in subparagraph (c) of this paragraph, it must be shown that –

(1)     The fuel jettisoning system and its operation are free from fire hazard;

(2)     The fuel discharges clear of any part of the aeroplane;

(3)     Fuel or fumes do not enter any parts of the aeroplane;

(4)     The jettisoning operation does not adversely affect the controllability of the aeroplane.

(e)     Reserved.

(f)      Means must be provided to prevent jettisoning the fuel in the tanks used for take-off and landing below the level allowing climb from sea level to 3048 m (10 000 ft) and thereafter allowing 45 minutes cruise at a speed for maximum range. However, if there is an auxiliary control independent of the main jettisoning control, the system may be designed to jettison the remaining fuel by means of the auxiliary jettisoning control.

(g)     The fuel jettisoning valve must be designed to allow flight personnel to close the valve during any part of the jettisoning operation.

(h)     Unless it is shown that using any means (including flaps, slots and slats) for changing the airflow across or around the wings does not adversely affect fuel jettisoning, there must be a placard, adjacent to the jettisoning control, to warn flight-crew members against jettisoning fuel while the means that change the airflow are being used.

(i)      The fuel jettisoning system must be designed so that any reasonably probable single malfunction in the system will not result in a hazardous condition due to unsymmetrical jettisoning of, or inability to jettison, fuel.