186
14 CFR Ch. I (1–1–14 Edition)
§ 23.21
less, a maximum certificated takeoff
weight of 12,500 pounds or less, and in-
tended for limited acrobatic operation.
Airplanes certificated in the utility
category may be used in any of the op-
erations covered under paragraph (a) of
this section and in limited acrobatic
operations. Limited acrobatic oper-
ation includes:
(1) Spins (if approved for the par-
ticular type of airplane); and
(2) Lazy eights, chandelles, and steep
turns, or similar maneuvers, in which
the angle of bank is more than 60 de-
grees but not more than 90 degrees.
(c) The acrobatic category is limited
to airplanes that have a seating con-
figuration, excluding pilot seats, of
nine or less, a maximum certificated
takeoff weight of 12,500 pounds or less,
and intended for use without restric-
tions, other than those shown to be
necessary as a result of required flight
tests.
(d) The commuter category is limited
to multiengine airplanes that have a
seating configuration, excluding pilot
seats, of 19 or less, and a maximum cer-
tificated takeoff weight of 19,000
pounds or less. The commuter category
operation is limited to any maneuver
incident to normal flying, stalls (ex-
cept whip stalls), and steep turns, in
which the angle of bank is not more
than 60 degrees.
(e) Except for commuter category,
airplanes may be type certificated in
more than one category if the require-
ments of each requested category are
met.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–4, 32 FR 5934, Apr. 14,
1967; Amdt. 23–34, 52 FR 1825, Jan. 15, 1987; 52
FR 34745, Sept. 14, 1987; Amdt. 23–50, 61 FR
5183, Feb. 9, 1996; Amdt. 23–62, 76 FR 75753,
Dec. 2, 2011]
Subpart B—Flight
G
ENERAL
§ 23.21
Proof of compliance.
(a) Each requirement of this subpart
must be met at each appropriate com-
bination of weight and center of grav-
ity within the range of loading condi-
tions for which certification is re-
quested. This must be shown—
(1) By tests upon an airplane of the
type for which certification is re-
quested, 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) The following general tolerances
are allowed during flight testing. How-
ever, greater tolerances may be al-
lowed in particular tests:
Item Tolerance
Weight ...............................................
+5%, –10%.
Critical items affected by weight .......
+5%, –1%.
C.G ....................................................
±
7% total travel.
§ 23.23
Load distribution limits.
(a) Ranges of weights and centers of
gravity within which the airplane may
be safely operated must be established.
If a weight and center of gravity com-
bination is allowable only within cer-
tain lateral load distribution limits
that could be inadvertently exceeded,
these limits must be established for the
corresponding weight and center of
gravity combinations.
(b) The load distribution limits may
not exceed any of the following:
(1) The selected limits;
(2) The limits at which the structure
is proven; or
(3) The limits at which compliance
with each applicable flight require-
ment of this subpart is shown.
[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]
§ 23.25
Weight limits.
(a)
Maximum weight. The maximum
weight is the highest weight at which
compliance with each applicable re-
quirement of this part (other than
those complied with at the design land-
ing weight) is shown. The maximum
weight must be established so that it
is—
(1) Not more than the least of—
(i) The highest weight selected by the
applicant; or
(ii) The design maximum weight,
which is the highest weight at which
compliance with each applicable struc-
tural loading condition of this part
(other than those complied with at the
design landing weight) is shown; or
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