105
Federal Aviation Administration, DOT
§ 121.201
(c) No zero fuel weight may be in-
creased by more than five percent, and
the increase in the structural landing
weight may not exceed the amount, in
pounds, of the increase in zero fuel
weight.
(d) Each airplane must be inspected
in accordance with the approved spe-
cial inspection procedures, for oper-
ations at increased weights, estab-
lished and issued by the manufacturer
of the type of airplane.
(e) Each airplane operated under this
section must be operated in accordance
with the passenger-carrying perform-
ance operating limitations prescribed
in this part.
(f) The Airplane Flight Manual for
each airplane operated under this sec-
tion must be appropriately revised to
include the operating limitations and
information needed for operation at
the increased weights.
(g) Except as provided for the car-
rying of persons under § 121.583 each
airplane operated at an increased
weight under this section must, before
it is used in passenger service, be in-
spected under the special inspection
procedures for return to passenger
service established and issued by the
manufacturer and approved by the Ad-
ministrator.
§ 121.199 Nontransport category air-
planes: Takeoff limitations.
(a) No person operating a non-
transport category airplane may take
off that airplane at a weight greater
than the weight that would allow the
airplane to be brought to a safe stop
within the effective length of the run-
way, from any point during the takeoff
before reaching 105 percent of min-
imum control speed (the minimum
speed at which an airplane can be safe-
ly controlled in flight after an engine
becomes inoperative) or 115 percent of
the power off stalling speed in the
takeoff configuration, whichever is
greater.
(b) For the purposes of this section—
(1) It may be assumed that takeoff
power is used on all engines during the
acceleration;
(2) Not more than 50 percent of the
reported headwind component, or not
less than 150 percent of the reported
tailwind component, may be taken into
account;
(3) The average runway gradient (the
difference between the elevations of
the endpoints of the runway divided by
the total length) must be considered if
it is more than one-half of 1 percent;
(4) It is assumed that the airplane is
operating in standard atmosphere; and
(5) The
effective length of the runway
for takeoff means the distance from
the end of the runway at which the
takeoff is started to a point at which
the obstruction clearance plane associ-
ated with the other end of the runway
intersects the runway centerline.
[Doc. No. 6258, 29 FR 19198, Dec. 31, 1964, as
amended by Amdt. 121–132, 41 FR 55475, Dec.
20, 1976]
§ 121.201 Nontransport category air-
planes: En route limitations: One
engine inoperative.
(a) Except as provided in paragraph
(b) of this section, no person operating
a nontransport category airplane may
take off that airplane at a weight that
does not allow a rate of climb of at
least 50 feet a minute, with the critical
engine inoperative, at an altitude of at
least 1,000 feet above the highest ob-
struction within five miles on each side
of the intended track, or 5,000 feet,
whichever is higher.
(b) Notwithstanding paragraph (a) of
this section, if the Administrator finds
that safe operations are not impaired,
a person may operate the airplane at
an altitude that allows the airplane, in
case of engine failure, to clear all ob-
structions within 5 miles on each side
of the intended track by 1,000 feet. If
this procedure is used, the rate of de-
scent for the appropriate weight and
altitude is assumed to be 50 feet a
minute greater than the rate in the ap-
proved performance data. Before ap-
proving such a procedure, the Adminis-
trator considers the following for the
route, route segment, or area con-
cerned:
(1) The reliability of wind and weath-
er forecasting.
(2) The location and kinds of naviga-
tion aids.
(3) The prevailing weather condi-
tions, particularly the frequency and
amount of turbulence normally en-
countered.
106
14 CFR Ch. I (1–1–24 Edition)
§ 121.203
(4) Terrain features.
(5) Air traffic control problems.
(6) Any other operational factors
that affect the operation.
(c) For the purposes of this section, it
is assumed that—
(1) The critical engine is inoperative;
(2) The propeller of the inoperative
engine is in the minimum drag posi-
tion;
(3) The wing flaps and landing gear
are in the most favorable position;
(4) The operating engines are oper-
ating at the maximum continuous
power available;
(5) The airplane is operating in stand-
ard atmosphere; and
(6) The weight of the airplane is pro-
gressively reduced by the anticipated
consumption of fuel and oil.
§ 121.203 Nontransport category air-
planes: Landing limitations: Des-
tination airport.
(a) No person operating a non-
transport category airplane may take
off that airplane at a weight that—
(1) Allowing for anticipated consump-
tion of fuel and oil, is greater than the
weight that would allow a full stop
landing within 60 percent of the effec-
tive length of the most suitable run-
way at the destination airport; and
(2) Is greater than the weight allow-
able if the landing is to be made on the
runway—
(i) With the greatest effective length
in still air; and
(ii) Required by the probable wind,
taking into account not more than 50
percent of the headwind component or
not less than 150 percent of the tail-
wind component.
(b) For the purposes of this section,
it is assumed that—
(1) The airplane passes directly over
the intersection of the obstruction
clearance plane and the runway at a
height of 50 feet in a steady gliding ap-
proach at a true indicated airspeed of
at least 1.3
V
So
;
(2) The landing does not require ex-
ceptional pilot skill; and
(3) The airplane is operating in stand-
ard atmosphere.
§ 121.205 Nontransport category air-
planes: Landing limitations: Alter-
nate airport.
No person may list an airport as an
alternate airport in a dispatch or flight
release for a nontransport category air-
plane unless that airplane (at the
weight anticipated at the time of ar-
rival) based on the assumptions con-
tained in § 121.203, can be brought to a
full stop landing within 70 percent of
the effective length of the runway.
§ 121.207 Provisionally certificated air-
planes: Operating limitations.
In addition to the limitations in
§ 91.317 of this chapter, the following
limitations apply to the operation of
provisionally certificated airplanes by
certificate holders:
(a) In addition to crewmembers, each
certificate holder may carry on such an
airplane only those persons who are
listed in § 121.547(c) or who are specifi-
cally authorized by both the certificate
holder and the Administrator.
(b) Each certificate holder shall keep
a log of each flight conducted under
this section and shall keep accurate
and complete records of each inspec-
tion made and all maintenance per-
formed on the airplane. The certificate
holder shall make the log and records
made under this section available to
the manufacturer and the Adminis-
trator.
[Doc. No. 28154, 61 FR 2611, Jan. 26, 1996]
Subpart J—Special Airworthiness
Requirements
S
OURCE
: Docket No. 6258, 29 FR 19202, Dec.
31, 1964, unless otherwise noted.
§ 121.211 Applicability.
(a) This subpart prescribes special
airworthiness requirements applicable
to certificate holders as stated in para-
graphs (b) through (e) of this section.
(b) Except as provided in paragraph
(d) of this section, each airplane type
certificated under Aero Bulletin 7A or
part 04 of the Civil Air Regulations in
effect before November 1, 1946 must
meet the special airworthiness require-
ments in §§ 121.215 through 121.283.