JAR 25.1001 Fuel jettisoning system
(a) A fuel jettisoning system must be
installed on each aeroplane unless it is shown that
the aeroplane meets the climb requirements of
JAR 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 JAR–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 JAR
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 wing-flaps
and landing gear up and in –
[(1) A power-off glide at 1·3 VSR1;]
(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 VSR1, 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 sub-paragraph
(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) Not required for JAR–25.
(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 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.
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