Section 25.5

14 CFR Ch. I (1-1-19 Edition)

(i) K25.1.4(a), fuel system pressure
and flow requirements;
(ii) K25.1.4(a)(3), low fuel alerting;
and
(iii) K25.1.4(c), engine oil tank design.
(2) For ETOPS type design approval
of an airplane beyond 180 minutes an
applicant must comply with Section 25.1535.
(c) Airplanes with more than two engines. An applicant for ETOPS type design approval must comply with
Section 25.1535 for an airplane manufactured
on or after February 17, 2015, except
that, for an airplane configured for a
three person flight crew, the applicant
need not comply with Appendix K,
K25.1.4(a)(3), of this part, low fuel alerting.

Subpart B - Flight

spaschal on DSK3GDR082PROD with CFR

[Doc. No. FAA-2002-6717, 72 FR 1873, Jan. 16,
2007]

Section 25.5 Incorporations by reference.
(a) The materials listed in this section are incorporated by reference in
the corresponding sections noted.
These incorporations by reference were
approved by the Director of the Federal
Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. These materials are incorporated as they exist on
the date of the approval, and notice of
any change in these materials will be
published in the FEDERAL REGISTER.
The materials are available for purchase at the corresponding addresses
noted below, and all are available for
inspection at the National Archives
and Records Administration (NARA).
For information on the availability of
this material at NARA, call 202-741-
6030, or go to: http://www.archives.gov/
federal-register/cfr/ibr-locations.html.
(b) The following materials are available for purchase from the following
address: The National Technical Information Services (NTIS), Springfield,
Virginia 22166.
(1) Fuel Tank Flammability Assessment Method User-s Manual, dated
May 2008, document number DOT/FAA/
AR-05/8, IBR approved for Section 25.981 and
Appendix N. It can also be obtained at
the
following
Web
site:
http://
www.fire.tc.faa.gov/systems/fueltank/
FTFAM.stm.
(2) [Reserved]
[73 FR 42494, July 21, 2008, as amended by
Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR
9169, Mar. 5, 2018]

GENERAL
Section 25.21

Proof of compliance.

(a) Each requirement of this subpart
must be met at each appropriate combination of weight and center of gravity within the range of loading conditions for which certification is requested. This must be shown - 
(1) By tests upon an airplane 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 center of gravity, if compliance
cannot be reasonably inferred from
combinations investigated.
(b) [Reserved]
(c) The controllability, stability,
trim, and stalling characteristics of
the airplane 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 (center of gravity and inertia), airspeed, power, and wind, must be maintained within acceptable tolerances of
the critical values during flight testing.
(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 SectionSection 25.671 and 25.672.
(f) In meeting the requirements of
SectionSection 25.105(d), 25.125, 25.233, and 25.237, the
wind velocity must be measured at a
height of 10 meters above the surface,
or corrected for the difference between
the height at which the wind velocity
is measured and the 10-meter height.
(g) The requirements of this subpart
associated with icing conditions apply
only if the applicant is seeking certification for flight in icing conditions.
(1) Paragraphs (g)(3) and (4) of this
section apply only to airplanes with
one or both of the following attributes:
(i) Maximum takeoff gross weight is
less than 60,000 lbs; or
(ii) The airplane is equipped with reversible flight controls.

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