ED
Decision 2016/010/R
(a) Each requirement of this Subpart must be
met at each appropriate combination of weight and centre of gravity within the
range of loading conditions for which certification is requested. This must be
shown –
(1) By tests upon an aeroplane of the type for
which certification is requested, or by calculations based on, and equal in
accuracy to, the results of testing; and
(2) By systematic investigation of each probable
combination of weight and centre of gravity, if compliance cannot be
reasonably inferred from combinations investigated.
(b) Reserved
(c) The controllability, stability, trim, and
stalling characteristics of the aeroplane must be shown for each altitude up
to the maximum expected in operation.
(d) Parameters critical for the test being
conducted, such as weight, loading (centre of gravity and inertia), airspeed,
power, and wind, must be maintained within acceptable tolerances of the
critical values during flight testing. (See AMC 25.21(d))
(e) If compliance with the flight
characteristics requirements is dependent upon a stability augmentation system
or upon any other automatic or power-operated system, compliance must be shown
with CS 25.671 and 25.672.
(f) In meeting the requirements of CS 25.105(d), 25.125, 25.233
and 25.237, the wind
velocity must be measured at a height of 10 metres above the surface, or
corrected for the difference between the height at which the wind velocity is
measured and the 10-metre height.
(g) The
requirements of this subpart associated with icing conditions apply only if
the applicant is seeking certification for flight in icing conditions. (See AMC 25.21(g))
(1) Each
requirement of this subpart, except CS
25.121(a), 25.123(c), 25.143(b)(1) and (b)(2), 25.149, 25.201(c)(2), and 25.251(b) through (e), must
be met in the icing
conditions specified
in Appendix C. CS 25.207(c) and (d) must be met in the landing
configuration in the icing conditions specified in Appendix C
but need not be met for other configurations. Compliance must be
shown using the ice accretions defined in part II of Appendix C,
assuming normal operation of the aeroplane and its ice protection system in
accordance with the operating limitations and operating procedures established
by the applicant and provided in the Aeroplane Flight Manual.
(2) If the applicant does not seek
certification for flight in all icing conditions defined in Appendix O,
each requirement of this subpart, except CS 25.105, 25.107, 25.109, 25.111, 25.113, 25.115, 25.121, 25.123, 25.143(b)(1), (b)(2), and (c)(1), 25.149, 25.201(c)(2), 25.207(c), (d) and (e)(1), and 25.251(b) through (e), must be met in the Appendix O
icing conditions for which certification is not sought in order to allow a
safe exit from those conditions. Compliance must be shown using the
iceaccretions defined in part II, paragraphs (b) and (d) of Appendix O,
assuming normal operation of the aeroplane and its ice protection system in
accordance with the operating limitations and operating procedures established
by the applicant and provided in the Aeroplane Flight Manual. If applicable, a
comparative analysis (refer to CS 25.1420) may be used to show compliance as
an alternative to using the ice accretions defined in part II,
paragraphs (b) and (d) of Appendix O.
(3) If the applicant seeks certification for
flight in any portion of the icing conditions of Appendix O, each requirement
of this subpart, except paragraphs CS 25.121(a), 25.123(c), 25.143(b)(1) and (b)(2), 25.149, 25.201(c)(2), and 25.251(b) through (e), must be met in the Appendix O icing conditions for which
certification is sought. CS 25.207(c) and (d) must be met in the landing
configuration in the icing conditions specified in Appendix O
for which certification is sought but need not be met for other
configurations. Compliance must be shown using the ice accretions defined in
part II, paragraphs (c) and (d) of Appendix O, assuming normal operation of the
aeroplane and its ice protection system in accordance with the operating
limitations and operating procedures established by the applicant and provided
in the Aeroplane Flight Manual. If applicable, a comparative analysis (refer
to CS 25.1420) may be used to show compliance as an alternative to using the
ice accretions defined in part II, paragraphs (c) and (d) of Appendix O.
(4) No
changes in the load distribution limits of CS 25.23, the weight limits
of CS 25.25 (except
where limited by performance requirements of this subpart), and the centre of
gravity limits of CS 25.27, from
those for non-icing conditions, are allowed for flight in icing conditions or
with ice accretion.
[Amdt
25/3]
[Amdt
25/6]
[Amdt
25/16]
[Amdt
25/17]
[Amdt
25/18]