286
14 CFR Ch. I (1–1–24 Edition)
§ 25.789
§ 25.789
Retention of items of mass in
passenger and crew compartments
and galleys.
(a) Means must be provided to pre-
vent each item of mass (that is part of
the airplane type design) in a passenger
or crew compartment or galley from
becoming a hazard by shifting under
the appropriate maximum load factors
corresponding to the specified flight
and ground load conditions, and to the
emergency landing conditions of
§ 25.561(b).
(b) Each interphone restraint system
must be designed so that when sub-
jected to the load factors specified in
§ 25.561(b)(3), the interphone will re-
main in its stowed position.
[Amdt. 25–32, 37 FR 3969, Feb. 24, 1972, as
amended by Amdt. 25–46, 43 FR 50596, Oct. 30,
1978]
§ 25.791
Passenger information signs
and placards.
(a) If smoking is to be prohibited,
there must be at least one placard so
stating that is legible to each person
seated in the cabin. If smoking is to be
allowed, and if the crew compartment
is separated from the passenger com-
partment, there must be at least one
sign notifying when smoking is prohib-
ited. Signs which notify when smoking
is prohibited must be operable by a
member of the flightcrew and, when il-
luminated, must be legible under all
probable conditions of cabin illumina-
tion to each person seated in the cabin.
(b) Signs that notify when seat belts
should be fastened and that are in-
stalled to comply with the operating
rules of this chapter must be operable
by a member of the flightcrew and,
when illuminated, must be legible
under all probable conditions of cabin
illumination to each person seated in
the cabin.
(c) A placard must be located on or
adjacent to the door of each receptacle
used for the disposal of flammable
waste materials to indicate that use of
the receptacle for disposal of ciga-
rettes, etc., is prohibited.
(d) Lavatories must have ‘‘No Smok-
ing’’ or ‘‘No Smoking in Lavatory’’
placards conspicuously located on or
adjacent to each side of the entry door.
(e) Symbols that clearly express the
intent of the sign or placard may be
used in lieu of letters.
[Amdt. 25–72, 55 FR 29780, July 20, 1990]
§ 25.793
Floor surfaces.
The floor surface of all areas which
are likely to become wet in service
must have slip resistant properties.
[Amdt. 25–51, 45 FR 7755, Feb. 4, 1980]
§ 25.795
Security considerations.
(a)
Protection of flightcrew compart-
ment. If a flightdeck door is required by
operating rules:
(1) The bulkhead, door, and any other
accessible boundary separating the
flightcrew compartment from occupied
areas must be designed to resist forc-
ible intrusion by unauthorized persons
and be capable of withstanding impacts
of 300 joules (221.3 foot pounds).
(2) The bulkhead, door, and any other
accessible boundary separating the
flightcrew compartment from occupied
areas must be designed to resist a con-
stant 250 pound (1,113 Newtons) tensile
load on accessible handholds, including
the doorknob or handle.
(3) The bulkhead, door, and any other
boundary separating the flightcrew
compartment from any occupied areas
must be designed to resist penetration
by small arms fire and fragmentation
devices to a level equivalent to level
IIIa of the National Institute of Justice
(NIJ) Standard 0101.04.
(4) If required by the operating rules
of this chapter, an installed physical
secondary barrier (IPSB) must be in-
stalled to resist intrusion into the
flightdeck whenever the flightdeck
door is opened. When deployed, the
IPSB must:
(i) Resist a 250 pound (1113 Newtons)
static load in the direction of the pas-
senger cabin applied at the most crit-
ical locations on the IPSB;
(ii) Resist a 600 pound (2669 Newtons)
static load in the direction of the
flightdeck applied at the most critical
locations on the IPSB;
(iii) Delay a person attempting to ac-
cess the flightdeck by at least the time
required for a crewmember to open and
reclose the flightdeck door, but no less
than 5 seconds;
VerDate Sep<11>2014
09:06 Jun 28, 2024
Jkt 262046
PO 00000
Frm 00296
Fmt 8010
Sfmt 8010
Y:\SGML\262046.XXX
262046
jspears on DSK121TN23PROD with CFR
287
Federal Aviation Administration, DOT
§ 25.795
(iv) Prevent a person from reaching
through and touching the flightdeck
door;
(v) Allow for necessary crewmember
activities; and
(vi) Provide line-of-sight visibility
between the flightdeck door and the
cabin.
(b) Airplanes with a maximum cer-
tificated passenger seating capacity of
more than 60 persons or a maximum
certificated takeoff gross weight of
over 100,000 pounds (45,359 Kilograms)
must be designed to limit the effects of
an explosive or incendiary device as
follows:
(1)
Flightdeck smoke protection. Means
must be provided to limit entry of
smoke, fumes, and noxious gases into
the flightdeck.
(2)
Passenger cabin smoke protection.
Means must be provided to prevent pas-
senger incapacitation in the cabin re-
sulting from smoke, fumes, and nox-
ious gases as represented by the initial
combined volumetric concentrations of
0.59% carbon monoxide and 1.23% car-
bon dioxide.
(3)
Cargo compartment fire suppression.
An extinguishing agent must be capa-
ble of suppressing a fire. All cargo-
compartment fire suppression systems
must be designed to withstand the fol-
lowing effects, including support struc-
ture displacements or adjacent mate-
rials displacing against the distribu-
tion system:
(i) Impact or damage from a 0.5-inch
diameter aluminum sphere traveling at
430 feet per second (131.1 meters per
second);
(ii) A 15-pound per square-inch (103.4
kPa) pressure load if the projected sur-
face area of the component is greater
than 4 square feet. Any single dimen-
sion greater than 4 feet (1.22 meters)
may be assumed to be 4 feet (1.22 me-
ters) in length; and
(iii) A 6-inch (0.152 meters) displace-
ment, except where limited by the fu-
selage contour, from a single point
force applied anywhere along the dis-
tribution system where relative move-
ment between the system and its at-
tachment can occur.
(iv) Paragraphs (b)(3)(i) through (iii)
of this section do not apply to compo-
nents that are redundant and separated
in accordance with paragraph (c)(2) of
this section or are installed remotely
from the cargo compartment.
(c) An airplane with a maximum cer-
tificated passenger seating capacity of
more than 60 persons or a maximum
certificated takeoff gross weight of
over 100,000 pounds (45,359 Kilograms)
must comply with the following:
(1)
Least risk bomb location. An air-
plane must be designed with a des-
ignated location where a bomb or other
explosive device could be placed to best
protect flight-critical structures and
systems from damage in the case of
detonation.
(2)
Survivability of systems. (i) Except
where impracticable, redundant air-
plane systems necessary for continued
safe flight and landing must be phys-
ically separated, at a minimum, by an
amount equal to a sphere of diameter
D
H
=
(
)
2
0
/
π
(where H
0
is defined under § 25.365(e)(2)
of this part and D need not exceed 5.05
feet (1.54 meters)). The sphere is ap-
plied everywhere within the fuselage—
limited by the forward bulkhead and
the aft bulkhead of the passenger cabin
and cargo compartment beyond which
only one-half the sphere is applied.
(ii) Where compliance with paragraph
(c)(2)(i) of this section is impracticable,
other design precautions must be taken
to maximize the survivability of those
systems.
(3)
Interior design to facilitate searches.
Design features must be incorporated
that will deter concealment or promote
discovery of weapons, explosives, or
other objects from a simple inspection
in the following areas of the airplane
cabin:
(i) Areas above the overhead bins
must be designed to prevent objects
from being hidden from view in a sim-
ple search from the aisle. Designs that
prevent concealment of objects with
volumes 20 cubic inches and greater
satisfy this requirement.
(ii) Toilets must be designed to pre-
vent the passage of solid objects great-
er than 2.0 inches in diameter.
(iii) Life preservers or their storage
locations must be designed so that
tampering is evident.
(d) Each chemical oxygen generator
or its installation must be designed to
VerDate Sep<11>2014
09:06 Jun 28, 2024
Jkt 262046
PO 00000
Frm 00297
Fmt 8010
Sfmt 8010
Y:\SGML\262046.XXX
262046
ER28OC08.003</MATH>
jspears on DSK121TN23PROD with CFR
288
14 CFR Ch. I (1–1–24 Edition)
§ 25.801
be secure from deliberate manipulation
by one of the following:
(1) By providing effective resistance
to tampering,
(2) By providing an effective com-
bination of resistance to tampering and
active tamper-evident features,
(3) By installation in a location or
manner whereby any attempt to access
the generator would be immediately
obvious, or
(4) By a combination of approaches
specified in paragraphs (d)(1), (d)(2) and
(d)(3) of this section that the Adminis-
trator finds provides a secure installa-
tion.
(e)
Exceptions. Airplanes used solely
to transport cargo only need to meet
the requirements of paragraphs (b)(1),
(b)(3), and (c)(2) of this section.
(f)
Material Incorporated by Reference.
You must use National Institute of
Justice (NIJ) Standard 0101.04, Ballistic
Resistance of Personal Body Armor,
June 2001, Revision A, to establish bal-
listic resistance as required by para-
graph (a)(3) of this section.
(1) The Director of the Federal Reg-
ister approved the incorporation by ref-
erence of this document under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) You may review copies of NIJ
Standard 0101.04 at the:
(i) National Institute of Justice
(NIJ),
http://www.ojp.usdoj.gov/nij, tele-
phone (202) 307–2942; or
(ii) National Archives and Records
Administration (NARA). For informa-
tion on the availability of this mate-
rial at NARA, call (202) 741–6030, or go
to
http://www.archives.gov/federal-reg-
ister/cfr/ibr-locations.html.
(3) You may obtain copies of NIJ
Standard 0101.04 from the National
Criminal Justice Reference Service,
P.O. Box 6000, Rockville, MD 20849–6000,
telephone (800) 851–3420.
[Amdt. 25–127; 121–341, 73 FR 63879, Oct. 28,
2008, as amended at 74 FR 22819, May 15, 2009;
Amdt. 25–138, 79 FR 13519, Mar. 11, 2014; Doc.
No. FAA–2018–0119, Amdt. 25–145, 83 FR 9169,
Mar. 5, 2018; Amdt. 25–150, 88 FR 41308, June
26, 2023]
E
MERGENCY
P
ROVISIONS
§ 25.801
Ditching.
(a) If certification with ditching pro-
visions is requested, the airplane must
meet the requirements of this section
and §§ 25.807(e), 25.1411, and 25.1415(a).
(b) Each practicable design measure,
compatible with the general character-
istics of the airplane, must be taken to
minimize the probability that in an
emergency landing on water, the be-
havior of the airplane would cause im-
mediate injury to the occupants or
would make it impossible for them to
escape.
(c) The probable behavior of the air-
plane in a water landing must be inves-
tigated by model tests or by compari-
son with airplanes of similar configura-
tion for which the ditching characteris-
tics are known. Scoops, flaps, projec-
tions, and any other factor likely to af-
fect the hydrodynamic characteristics
of the airplane, must be considered.
(d) It must be shown that, under rea-
sonably probable water conditions, the
flotation time and trim of the airplane
will allow the occupants to leave the
airplane and enter the liferafts re-
quired by § 25.1415. If compliance with
this provision is shown by buoyancy
and trim computations, appropriate al-
lowances must be made for probable
structural damage and leakage. If the
airplane has fuel tanks (with fuel jetti-
soning provisions) that can reasonably
be expected to withstand a ditching
without leakage, the jettisonable vol-
ume of fuel may be considered as buoy-
ancy volume.
(e) Unless the effects of the collapse
of external doors and windows are ac-
counted for in the investigation of the
probable behavior of the airplane in a
water landing (as prescribed in para-
graphs (c) and (d) of this section), the
external doors and windows must be
designed to withstand the probable
maximum local pressures.
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–72, 55 FR 29781, July 20,
1990]
§ 25.803
Emergency evacuation.
(a) Each crew and passenger area
must have emergency means to allow
rapid evacuation in crash landings,
with the landing gear extended as well
as with the landing gear retracted, con-
sidering the possibility of the airplane
being on fire.
(b) [Reserved]
VerDate Sep<11>2014
09:06 Jun 28, 2024
Jkt 262046
PO 00000
Frm 00298
Fmt 8010
Sfmt 8010
Y:\SGML\262046.XXX
262046
jspears on DSK121TN23PROD with CFR