title-14-part-25-sec25-1419

355

Federal Aviation Administration, DOT

§ 25.1419

AFETY

QUIPMENT

§ 25.1411

General.

(a)

Accessibility.

Required safety

equipment to be used by the crew in an
emergency must be readily accessible.

(b)

Stowage provisions. Stowage provi-

sions for required emergency equip-
ment must be furnished and must—

(1) Be arranged so that the equip-

ment is directly accessible and its loca-
tion is obvious; and

(2) Protect the safety equipment

from inadvertent damage.

(c)

Emergency exit descent device. The

stowage provisions for the emergency
exit descent devices required by
§ 25.810(a) must be at each exit for
which they are intended.

(d)

Liferafts. (1) The stowage provi-

sions for the liferafts described in
§ 25.1415 must accommodate enough
rafts for the maximum number of occu-
pants for which certification for ditch-
ing is requested.

(2) Liferafts must be stowed near

exits through which the rafts can be
launched during an unplanned ditch-
ing.

(3) Rafts automatically or remotely

released outside the airplane must be
attached to the airplane by means of
the static line prescribed in § 25.1415.

(4) The stowage provisions for each

portable liferaft must allow rapid de-
tachment and removal of the raft for
use at other than the intended exits.

(e)

Long-range signaling device. The

stowage provisions for the long-range
signaling device required by § 25.1415
must be near an exit available during
an unplanned ditching.

(f)

Life preserver stowage provisions.

The stowage provisions for life pre-
servers described in § 25.1415 must ac-
commodate one life preserver for each
occupant for which certification for
ditching is requested. Each life pre-
server must be within easy reach of
each seated occupant.

(g)

Life line stowage provisions. If cer-

tification for ditching under § 25.801 is
requested, there must be provisions to
store life lines. These provisions
must—

(1) Allow one life line to be attached

to each side of the fuselage; and

(2) Be arranged to allow the life lines

to be used to enable the occupants to
stay on the wing after ditching.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–32, 37 FR 3972, Feb. 24,
1972; Amdt. 25–46, 43 FR 50598, Oct. 30, 1978;
Amdt. 25–53, 45 FR 41593, June 19, 1980; Amdt.
25–70, 54 FR 43925, Oct. 27, 1989; Amdt. 25–79,
58 FR 45229, Aug. 26, 1993; Amdt. 25–116, 69 FR
62789, Oct. 27, 2004]

§ 25.1415

Ditching equipment.

(a) Ditching equipment used in air-

planes to be certificated for ditching
under § 25.801, and required by the oper-
ating rules of this chapter, must meet
the requirements of this section.

(b) Each liferaft and each life pre-

server must be approved. In addition—

(1) Unless excess rafts of enough ca-

pacity are provided, the buoyancy and
seating capacity beyond the rated ca-
pacity of the rafts must accommodate
all occupants of the airplane in the
event of a loss of one raft of the largest
rated capacity; and

(2) Each raft must have a trailing

line, and must have a static line de-
signed to hold the raft near the air-
plane but to release it if the airplane
becomes totally submerged.

must be attached to each liferaft.

(d) There must be an approved sur-

vival type emergency locator trans-
mitter for use in one life raft.

(e) For airplanes not certificated for

ditching under § 25.801 and not having
approved life preservers, there must be
an approved flotation means for each
occupant. This means must be within
easy reach of each seated occupant and
must be readily removable from the
airplane.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–29, 36 FR 18722, Sept.
21, 1971; Amdt. 25–50, 45 FR 38348, June 9, 1980;
Amdt. 25–72, 55 FR 29785, July 20, 1990; Amdt.
25–82, 59 FR 32057, June 21, 1994]

§ 25.1419

Ice protection.

If the applicant seeks certification

for flight in icing conditions, the air-
plane must be able to safely operate in
the continuous maximum and inter-
mittent maximum icing conditions of
appendix C. To establish this—

(a) An analysis must be performed to

establish that the ice protection for

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14 CFR Ch. I (1–1–24 Edition)

§ 25.1420

the various components of the airplane
is adequate, taking into account the
various airplane operational configura-
tions; and

(b) To verify the ice protection anal-

ysis, to check for icing anomalies, and
to demonstrate that the ice protection
system and its components are effec-
tive, the airplane or its components
must be flight tested in the various
operational configurations, in meas-
ured natural atmospheric icing condi-
tions and, as found necessary, by one
or more of the following means:

(1) Laboratory dry air or simulated

icing tests, or a combination of both, of
the components or models of the com-
ponents.

(2) Flight dry air tests of the ice pro-

tection system as a whole, or of its in-
dividual components.

(3) Flight tests of the airplane or its

components in measured simulated
icing conditions.

amber caution light or equivalent,
must be provided to alert the
flightcrew when the anti-ice or de-ice
system is not functioning normally.

(d) For turbine engine powered air-

planes, the ice protection provisions of
this section are considered to be appli-
cable primarily to the airframe. For
the powerplant installation, certain ad-
ditional provisions of subpart E of this
part may be found applicable.

(e) One of the following methods of

icing detection and activation of the
airframe ice protection system must be
provided:

(1) A primary ice detection system

that automatically activates or alerts
the flightcrew to activate the airframe
ice protection system;

(2) A definition of visual cues for rec-

ognition of the first sign of ice accre-
tion on a specified surface combined
with an advisory ice detection system
that alerts the flightcrew to activate
the airframe ice protection system; or

(3) Identification of conditions con-

ducive to airframe icing as defined by
an appropriate static or total air tem-
perature and visible moisture for use
by the flightcrew to activate the air-
frame ice protection system.

(f) Unless the applicant shows that

the airframe ice protection system
need not be operated during specific

phases of flight, the requirements of
paragraph (e) of this section are appli-
cable to all phases of flight.

(g) After the initial activation of the

airframe ice protection system—

(1) The ice protection system must be

designed to operate continuously;

(2) The airplane must be equipped

with a system that automatically cy-
cles the ice protection system; or

(3) An ice detection system must be

provided to alert the flightcrew each
time the ice protection system must be
cycled.

(h) Procedures for operation of the

ice protection system, including acti-
vation and deactivation, must be estab-
lished and documented in the Airplane
Flight Manual.

[Amdt. 25–72, 55 FR 29785, July 20, 1990, as
amended by Amdt. 25–121, 72 FR 44669, Aug. 8,
2007; Amdt. 25–129, 74 FR 38339, Aug. 3, 2009]

§ 25.1420

Supercooled large drop icing

conditions.

(a) If certification for flight in icing

conditions is sought, in addition to the
requirements of § 25.1419, an airplane
with a maximum takeoff weight less
than 60,000 pounds or with reversible
flight controls must be capable of oper-
ating in accordance with paragraphs
(a)(1), (2), or (3), of this section.

(1) Operating safely after encoun-

tering the icing conditions defined in
Appendix O of this part:

(i) The airplane must have a means

to detect that it is operating in Appen-
dix O icing conditions; and

(ii) Following detection of Appendix

O icing conditions, the airplane must
be capable of operating safely while
exiting all icing conditions.

(2) Operating safely in a portion of

the icing conditions defined in Appen-
dix O of this part as selected by the ap-
plicant:

(i) The airplane must have a means

to detect that it is operating in condi-
tions that exceed the selected portion
of Appendix O icing conditions; and

(ii) Following detection, the airplane

must be capable of operating safely
while exiting all icing conditions.

(3) Operating safely in the icing con-

ditions defined in Appendix O of this
part.

(b) To establish that the airplane can

operate safely as required in paragraph