ED
Decision 2014/026/R
(a) If certification with ditching provisions
is requested, the aeroplane must meet the requirements of this paragraph and CS 25.807(i),
25.1411 and
25.1415(a).
(b) Each practicable design measure,
compatible with the general characteristics of the aeroplane, must be taken to
minimise the probability that in an emergency landing on water, the behaviour
of the aeroplane would cause immediate injury to the occupants or would make
it impossible for them to escape.
(c) The probable behaviour of the aeroplane
in a water landing must be investigated by model tests or by comparison with
aeroplanes of similar configuration for which the ditching characteristics are
known. Scoops, wing-flaps, projections, and any other factor likely to affect
the hydrodynamic characteristics of the aeroplane, must be considered.
(d) It must be shown that, under reasonably
probable water conditions, the flotation time and trim of the aeroplane will
allow the occupants to leave the aeroplane and enter the life rafts required
by CS 25.1415. If compliance with this provision is shown
by buoyancy and trim computations, appropriate allowances must be made for
probable structural damage and leakage. If the aeroplane has fuel tanks (with
fuel jettisoning provisions) that can reasonably be expected to withstand a
ditching without leakage, the jettisonable volume of fuel may be considered as
buoyancy volume.
(e) Unless the effects of the collapse of
external doors and windows are accounted for in the investigation of the
probable behaviour of the aeroplane in a water landing (as prescribed in sub-paragraphs
(c) and (d) of this paragraph), the external doors and windows must be
designed to withstand the probable maximum local pressures.
[Amdt
25/15]
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