title-14-part-25-sec25-1533

367

Federal Aviation Administration, DOT

§ 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

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.

(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

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14 CFR Ch. I (1–1–24 Edition)

§ 25.1535

which compliance is shown with the
applicable provisions of this part (in-
cluding the landing and approach climb
provisions of §§ 25.119 and 25.121(d) for
altitudes and ambient temperatures).

(3) The minimum takeoff distances

must be established as the distances at
which compliance is shown with the
applicable provisions of this part (in-
cluding the provisions of §§ 25.109 and
25.113, for weights, altitudes, tempera-
tures, wind components, runway sur-
face conditions (dry and wet), and run-
way gradients) for smooth, hard-sur-
faced runways. Additionally, at the op-
tion of the applicant, wet runway take-
off distances may be established for
runway surfaces that have been
grooved or treated with a porous fric-
tion course, and may be approved for
use on runways where such surfaces
have been designed constructed, and
maintained in a manner acceptable to
the Administrator.

(b) The extremes for variable factors

(such as altitude, temperature, wind,
and runway gradients) are those at
which compliance with the applicable
provisions of this part is shown.

ance with § 25.1420(a)(1) or (2), an oper-
ating limitation must be established
to:

(1) Prohibit intentional flight, in-

cluding takeoff and landing, into icing
conditions defined in Appendix O of
this part for which the airplane has not
been certified to safely operate; and

(2) Require exiting all icing condi-

tions if icing conditions defined in Ap-
pendix O of this part are encountered
for which the airplane has not been
certified to safely operate.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–38, 41 FR 55468, Dec. 20,
1976; Amdt. 25–72, 55 FR 29786, July 20, 1990;
Amdt. 25–92, 63 FR 8321, Feb. 18, 1998; Amdt.
25–140, 79 FR 65528, Nov. 4, 2014]

§ 25.1535

ETOPS approval.

Except as provided in § 25.3, each ap-

plicant seeking ETOPS type design ap-
proval must comply with the provi-
sions of Appendix K of this part.

[Doc. No. FAA–2002–6717, 72 FR 1873, Jan. 16,
2007]

ARKINGS AND

LACARDS

§ 25.1541

General.

(a) The airplane must contain—
(1) The specified markings and plac-

ards; and

(2) Any additional information, in-

strument markings, and placards re-
quired for the safe operation if there
are unusual design, operating, or han-
dling characteristics.

(b) Each marking and placard pre-

scribed in paragraph (a) of this sec-
tion—

(1) Must be displayed in a con-

spicuous place; and

(2) May not be easily erased, dis-

figured, or obscured.

§ 25.1543

Instrument markings: gen-

eral.

For each instrument—
(a) When markings are on the cover

glass of the instrument, there must be
means to maintain the correct align-
ment of the glass cover with the face of
the dial; and

(b) Each instrument marking must

be clearly visible to the appropriate
crewmember.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–72, 55 FR 29786, July 20,
1990]

§ 25.1545

Airspeed limitation informa-

tion.

The airspeed limitations required by

§ 25.1583 (a) must be easily read and un-
derstood by the flight crew.

§ 25.1547

Magnetic direction indicator.

(a) A placard meeting the require-

ments of this section must be installed
on, or near, the magnetic direction in-
dicator.

(b) The placard must show the cali-

bration of the instrument in level
flight with the engines operating.

the calibration was made with radio re-
ceivers on or off.

(d) Each calibration reading must be

in terms of magnetic heading in not
more than 45 degree increments.