title-14-part-25-sec25-1521

366

14 CFR Ch. I (1–1–24 Edition)

§ 25.1507

Maneuvering speed.

The maneuvering speed must be es-

tablished so that it does not exceed the
design maneuvering speed

deter-

mined under § 25.335(c).

§ 25.1511

Flap extended speed.

The established flap extended speed

must be established so that it does

not exceed the design flap speed

chosen under §§ 25.335(e) and 25.345, for
the corresponding flap positions and
engine powers.

§ 25.1513

Minimum control speed.

The minimum control speed

de-

termined under § 25.149 must be estab-
lished as an operating limitation.

§ 25.1515

Landing gear speeds.

(a) The established landing gear oper-

ating speed or speeds,

LO,

may not ex-

ceed the speed at which it is safe both
to extend and to retract the landing
gear, as determined under § 25.729 or by
flight characteristics. If the extension
speed is not the same as the retraction
speed, the two speeds must be des-
ignated as

(

EXT

)

and

(

RET

)

respec-

tively.

(b) The established landing gear ex-

tended speed

may not exceed the

speed at which it is safe to fly with the
landing gear secured in the fully ex-
tended position, and that determined
under § 25.729.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–38, 41 FR 55468, Dec. 20,
1976]

§ 25.1516

Other speed limitations.

Any other limitation associated with

speed must be established.

[Doc. No. 2000–8511, 66 FR 34024, June 26, 2001]

§ 25.1517

Rough air speed, V

RA.

(a) A rough air speed, V

RA,

for use as

the recommended turbulence penetra-
tion airspeed, and a rough air Mach
number, M

, for use as the rec-

ommended turbulence penetration
Mach number, must be established.
V

must be sufficiently less than

to ensure that likely speed

variation during rough air encounters
will not cause the overspeed warning to
operate too frequently.

(b) At altitudes where V

is not lim-

ited by Mach number, in the absence of
a rational investigation substantiating
the use of other values, V

must be

less than V

minus 35 KTAS.

is limited

by Mach number, M

may be chosen

to provide an optimum margin between
low and high speed buffet boundaries.

[Amdt. 25–141, 79 FR 73469, Dec. 11, 2014, as
amended by FAA–2022–1355; Amdt. No. 25–148,
87 FR 75710, Dec. 9, 2022; 88 FR 2813, Jan. 18,
2023]

§ 25.1519

Weight, center of gravity, and

weight distribution.

The airplane weight, center of grav-

ity, and weight distribution limita-
tions determined under §§ 25.23 through
25.27 must be established as operating
limitations.

§ 25.1521

Powerplant limitations.

(a)

General. The powerplant limita-

tions prescribed in this section must be
established so that they do not exceed
the corresponding limits for which the
engines or propellers are type certifi-
cated and do not exceed the values on
which compliance with any other re-
quirement of this part is based.

(b)

Reciprocating engine installations.

Operating limitations relating to the
following must be established for recip-
rocating engine installations:

(1) Horsepower or torque, r.p.m.,

manifold pressure, and time at critical
pressure altitude and sea level pressure
altitude for—

(i) Maximum continuous power (re-

lating to unsupercharged operation or
to operation in each supercharger mode
as applicable); and

(ii) Takeoff power (relating to unsu-

percharged operation or to operation in
each supercharger mode as applicable).

(2) Fuel grade or specification.
(3) Cylinder head and oil tempera-

tures.

(4) Any other parameter for which a

limitation has been established as part
of the engine type certificate except
that a limitation need not be estab-
lished for a parameter that cannot be
exceeded during normal operation due
to the design of the installation or to
another established limitation.

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§ 25.1533

(c)

Turbine engine installations. Oper-

ating limitations relating to the fol-
lowing must be established for turbine
engine installations:

(1) Horsepower, torque or thrust,

r.p.m., gas temperature, and time for—

(i) Maximum continuous power or

thrust (relating to augmented or un-
augmented operation as applicable).

(ii) Takeoff power or thrust (relating

to augmented or unaugmented oper-
ation as applicable).

(2) Fuel designation or specification.
(3) Maximum time interval between

engine run-ups from idle, run-up power
setting and duration at power for
ground operation in icing conditions,
as defined in § 25.1093(b)(2).

(4) Any other parameter for which a

(d)

Ambient temperature. An ambient

temperature limitation (including lim-
itations for winterization installations,
if applicable) must be established as
the maximum ambient atmospheric
temperature established in accordance
with § 25.1043(b).

[Amdt. 25–72, 55 FR 29786, July 20, 1990, as
amended by Amdt. 25–140, 79 FR 65528, Nov. 4,
2014]

§ 25.1522

Auxiliary power unit limita-

tions.

If an auxiliary power unit is installed

in the airplane, limitations established
for the auxiliary power unit, including
categories of operation, must be speci-
fied as operating limitations for the
airplane.

[Amdt. 25–72, 55 FR 29786, July 20, 1990]

§ 25.1523

Minimum flight crew.

The minimum flight crew must be es-

tablished so that it is sufficient for safe
operation, considering—

(a) The workload on individual crew-

members;

(b) The accessibility and ease of oper-

ation of necessary controls by the ap-
propriate crewmember; and

under § 25.1525.

The criteria used in making the deter-
minations required by this section are
set forth in appendix D.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–3, 30 FR 6067, Apr. 29,
1965]

§ 25.1525

Kinds of operation.

The kinds of operation to which the

airplane is limited are established by
the category in which it is eligible for
certification and by the installed
equipment.

§ 25.1527

Ambient air temperature and

operating altitude.

The extremes of the ambient air tem-

perature and operating altitude for
which operation is allowed, as limited
by flight, structural, powerplant, func-
tional, or equipment characteristics,
must be established.

[Doc. No. 2000–8511, 66 FR 34024, June 26, 2001]

§ 25.1529

Instructions for Continued

Airworthiness.

The applicant must prepare Instruc-

tions for Continued Airworthiness in
accordance with appendix H to this
part that are acceptable to the Admin-
istrator. The instructions may be in-
complete at type certification if a pro-
gram exists to ensure their completion
prior to delivery of the first airplane or
issuance of a standard certificate of
airworthiness, whichever occurs later.

[Amdt. 25–54, 45 FR 60173, Sept. 11, 1980]

§ 25.1531

Maneuvering flight load fac-

tors.

Load factor limitations, not exceed-

ing the positive limit load factors de-
termined from the maneuvering dia-
gram in § 25.333(b), must be established.

§ 25.1533

Additional operating limita-

tions.

(a) Additional operating limitations

must be established as follows:

(1) The maximum takeoff weights

must be established as the weights at
which compliance is shown with the
applicable provisions of this part (in-
cluding the takeoff climb provisions of
§ 25.121(a) through (c), for altitudes and
ambient temperatures).

(2) The maximum landing weights

must be established as the weights at