210
14 CFR Ch. I (1–1–14 Edition)
§ 23.303
(a) Meet all requirements of subpart
C and subpart D of this part applicable
to a wing; and
(b) Meet all requirements applicable
to the function performed by these sur-
faces.
[Amdt. 23–42, 56 FR 352, Jan. 3, 1991]
§ 23.303
Factor of safety.
Unless otherwise provided, a factor of
safety of 1.5 must be used.
§ 23.305
Strength and deformation.
(a) The structure must be able to
support limit loads without detri-
mental, permanent deformation. At
any load up to limit loads, the defor-
mation may not interfere with safe op-
eration.
(b) The structure must be able to
support ultimate loads without failure
for at least three seconds, except local
failures or structural instabilities be-
tween limit and ultimate load are ac-
ceptable only if the structure can sus-
tain the required ultimate load for at
least three seconds. However when
proof of strength is shown by dynamic
tests simulating actual load condi-
tions, the three second limit does not
apply.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–45, 58 FR 42160, Aug. 6,
1993]
§ 23.307
Proof of structure.
(a) Compliance with the strength and
deformation requirements of § 23.305
must be shown for each critical load
condition. Structural analysis may be
used only if the structure conforms to
those for which experience has shown
this method to be reliable. In other
cases, substantiating load tests must
be made. Dynamic tests, including
structural flight tests, are acceptable if
the design load conditions have been
simulated.
(b) Certain parts of the structure
must be tested as specified in Subpart
D of this part.
F
LIGHT
L
OADS
§ 23.321
General.
(a) Flight load factors represent the
ratio of the aerodynamic force compo-
nent (acting normal to the assumed
longitudinal axis of the airplane) to the
weight of the airplane. A positive flight
load factor is one in which the aero-
dynamic force acts upward, with re-
spect to the airplane.
(b) Compliance with the flight load
requirements of this subpart must be
shown—
(1) At each critical altitude within
the range in which the airplane may be
expected to operate;
(2) At each weight from the design
minimum weight to the design max-
imum weight; and
(3) For each required altitude and
weight, for any practicable distribution
of disposable load within the operating
limitations specified in §§ 23.1583
through 23.1589.
(c) When significant, the effects of
compressibility must be taken into ac-
count.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–45, 58 FR 42160, Aug. 6,
1993]
§ 23.331
Symmetrical flight conditions.
(a) The appropriate balancing hori-
zontal tail load must be accounted for
in a rational or conservative manner
when determining the wing loads and
linear inertia loads corresponding to
any of the symmetrical flight condi-
tions specified in §§ 23.333 through
23.341.
(b) The incremental horizontal tail
loads due to maneuvering and gusts
must be reacted by the angular inertia
of the airplane in a rational or conserv-
ative manner.
(c) Mutual influence of the aero-
dynamic surfaces must be taken into
account when determining flight loads.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30
FR 258, Jan. 9, 1965, as amended by Amdt. 23–
42, 56 FR 352, Jan. 3, 1991]
§ 23.333
Flight envelope.
(a)
General. Compliance with the
strength requirements of this subpart
must be shown at any combination of
airspeed and load factor on and within
the boundaries of a flight envelope
(similar to the one in paragraph (d) of
this section) that represents the enve-
lope of the flight loading conditions
specified by the maneuvering and gust
criteria of paragraphs (b) and (c) of this
section respectively.
VerDate Mar<15>2010
10:12 Mar 18, 2014
Jkt 232046
PO 00000
Frm 00220
Fmt 8010
Sfmt 8010
Y:\SGML\232046.XXX
232046
pmangrum on DSK3VPTVN1PROD with CFR