187
Federal Aviation Administration, DOT
§ 23.33
(iii) The highest weight at which
compliance with each applicable flight
requirement is shown, and
(2) Not less than the weight with—
(i) Each seat occupied, assuming a
weight of 170 pounds for each occupant
for normal and commuter category air-
planes, and 190 pounds for utility and
acrobatic category airplanes, except
that seats other than pilot seats may
be placarded for a lesser weight; and
(A) Oil at full capacity, and
(B) At least enough fuel for max-
imum continuous power operation of at
least 30 minutes for day-VFR approved
airplanes and at least 45 minutes for
night-VFR and IFR approved airplanes;
or
(ii) The required minimum crew, and
fuel and oil to full tank capacity.
(b)
Minimum weight. The minimum
weight (the lowest weight at which
compliance with each applicable re-
quirement of this part is shown) must
be established so that it is not more
than the sum of—
(1) The empty weight determined
under § 23.29;
(2) The weight of the required min-
imum crew (assuming a weight of 170
pounds for each crewmember); and
(3) The weight of—
(i) For turbojet powered airplanes, 5
percent of the total fuel capacity of
that particular fuel tank arrangement
under investigation, and
(ii) For other airplanes, the fuel nec-
essary for one-half hour of operation at
maximum continuous power.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–7, 34 FR 13086, Aug. 13,
1969; Amdt. 23–21, 43 FR 2317, Jan. 16, 1978;
Amdt. 23–34, 52 FR 1825, Jan. 15, 1987; Amdt.
23–45, 58 FR 42156, Aug. 6, 1993; Amdt. 23–50, 61
FR 5183, Feb. 9, 1996]
§ 23.29
Empty weight and cor-
responding center of gravity.
(a) The empty weight and cor-
responding center of gravity must be
determined by weighing the airplane
with—
(1) Fixed ballast;
(2) Unusable fuel determined under
§ 23.959; and
(3) Full operating fluids, including—
(i) Oil;
(ii) Hydraulic fluid; and
(iii) Other fluids required for normal
operation of airplane systems, except
potable water, lavatory precharge
water, and water intended for injection
in the engines.
(b) The condition of the airplane at
the time of determining empty weight
must be one that is well defined and
can be easily repeated.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30
FR 258, Jan. 9, 1965, as amended by Amdt. 23–
21, 43 FR 2317, Jan. 16, 1978]
§ 23.31
Removable ballast.
Removable ballast may be used in
showing compliance with the flight re-
quirements of this subpart, if—
(a) The place for carrying ballast is
properly designed and installed, and is
marked under § 23.1557; and
(b) Instructions are included in the
airplane flight manual, approved man-
ual material, or markings and plac-
ards, for the proper placement of the
removable ballast under each loading
condition for which removable ballast
is necessary.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30
FR 258, Jan. 9, 1965, as amended by Amdt. 23–
13, 37 FR 20023, Sept. 23, 1972]
§ 23.33
Propeller speed and pitch lim-
its.
(a)
General. The propeller speed and
pitch must be limited to values that
will assure safe operation under normal
operating conditions.
(b)
Propellers not controllable in flight.
For each propeller whose pitch cannot
be controlled in flight—
(1) During takeoff and initial climb
at the all engine(s) operating climb
speed specified in § 23.65, the propeller
must limit the engine r.p.m., at full
throttle or at maximum allowable
takeoff manifold pressure, to a speed
not greater than the maximum allow-
able takeoff r.p.m.; and
(2) During a closed throttle glide, at
V
NE,
the propeller may not cause an
engine speed above 110 percent of max-
imum continuous speed.
(c)
Controllable pitch propellers without
constant speed controls. Each propeller
that can be controlled in flight, but
that does not have constant speed con-
trols, must have a means to limit the
pitch range so that—
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