125
Federal Aviation Administration, DOT
§ 121.312
equipped at each flight deck station
with a combined safety belt and shoul-
der harness that meets the applicable
requirements specified in § 25.785 of this
chapter, effective March 6, 1980, except
that—
(1) Shoulder harnesses and combined
safety belt and shoulder harnesses that
were approved and installed before
March 6, 1980, may continue to be used;
and
(2) Safety belt and shoulder harness
restraint systems may be designed to
the inertia load factors established
under the certification basis of the air-
plane.
(g) Each flight attendant must have a
seat for takeoff and landing in the pas-
senger compartment that meets the re-
quirements of § 25.785 of this chapter,
effective March 6, 1980, except that—
(1) Combined safety belt and shoulder
harnesses that were approved and in-
stalled before March, 6, 1980, may con-
tinue to be used; and
(2) Safety belt and shoulder harness
restraint systems may be designed to
the inertia load factors established
under the certification basis of the air-
plane.
(3) The requirements of § 25.785(h) do
not apply to passenger seats occupied
by flight attendants not required by
§ 121.391.
(h) Each occupant of a seat equipped
with a shoulder harness or with a com-
bined safety belt and shoulder harness
must have the shoulder harness or
combined safety belt and shoulder har-
ness properly secured about that occu-
pant during takeoff and landing, except
that a shoulder harness that is not
combined with a safety belt may be un-
fastened if the occupant cannot per-
form the required duties with the
shoulder harness fastened.
(i) At each unoccupied seat, the safe-
ty belt and shoulder harness, if in-
stalled, must be secured so as not to
interfere with crewmembers in the per-
formance of their duties or with the
rapid egress of occupants in an emer-
gency.
(j) After October 27, 2009, no person
may operate a transport category air-
plane type certificated after January 1,
1958 and manufactured on or after Oc-
tober 27, 2009 in passenger-carrying op-
erations under this part unless all pas-
senger and flight attendant seats on
the airplane meet the requirements of
§ 25.562 in effect on or after June 16,
1988.
(k)
Seat dimension disclosure.
(1) Each
air carrier that conducts operations
under this part and that has a Web site
must make available on its Web site
the width of the narrowest and widest
passenger seats in each class of service
for each airplane make, model and se-
ries operated by that air carrier in pas-
senger-carrying operations.
(2) For purposes of paragraph (k)(1) of
this section, the width of a passenger
seat means the distance between the
inside of the armrests for that seat.
[Doc. No. 7522, 32 FR 13267, Sept. 20, 1967]
E
DITORIAL
N
OTE
: For F
EDERAL
R
EGISTER
ci-
tations affecting § 121.311, see the List of CFR
Sections Affected, which appears in the
Finding Aids section of the printed volume
and at
www.govinfo.gov.
§ 121.312 Materials for compartment
interiors.
(a)
All interior materials; transport cat-
egory airplanes and nontransport cat-
egory airplanes type certificated before
January 1, 1965.
Except for the mate-
rials covered by paragraph (b) of this
section, all materials in each compart-
ment of a transport category airplane,
or a nontransport category airplane
type certificated before January 1, 1965,
used by the crewmembers and pas-
sengers, must meet the requirements of
§ 25.853 of this chapter in effect as fol-
lows, or later amendment thereto:
(1)
Airplane with passenger seating ca-
pacity of 20 or more
—(i)
Manufactured
after August 19, 1988, but prior to August
20, 1990.
Except as provided in para-
graph (a)(3)(ii) of this section, each air-
plane with a passenger capacity of 20 or
more and manufactured after August
19, 1988, but prior to August 20, 1990,
must comply with the heat release rate
testing provisions of § 25.853(d) in effect
March 6, 1995 (formerly § 25.853(a–1) in
effect on August 20, 1986) (see App. L of
this part), except that the total heat
release over the first 2 minutes of sam-
ple exposure must not exceed 100 kilo-
watt minutes per square meter and the
peak heat release rate must not exceed
100 kilowatts per square meter.
126
14 CFR Ch. I (1–1–24 Edition)
§ 121.312
(ii)
Manufactured after August 19, 1990.
Each airplane with a passenger capac-
ity of 20 or more and manufactured
after August 19, 1990, must comply with
the heat release rate and smoke testing
provisions of § 25.853(d) in effect March
6, 1995 (formerly § 25.853(a–1)(see app. L
of this part) in effect on September 26,
1988).
(2)
Substantially complete replacement
of the cabin interior on or after May 1,
1972
—(i)
Airplane for which the applica-
tion for type certificate was filed prior to
May 1, 1972.
Except as provided in para-
graph (a)(3)(i) or (a)(3)(ii) of this sec-
tion, each airplane for which the appli-
cation for type certificate was filed
prior to May 1, 1972, must comply with
the provisions of § 25.853 in effect on
April 30, 1972, regardless of passenger
capacity, if there is a substantially
complete replacement of the cabin in-
terior after April 30, 1972.
(ii)
Airplane for which the application
for type certificate was filed on or after
May 1, 1972.
Except as provided in para-
graph (a)(3)(i) or (a)(3)(ii) of this sec-
tion, each airplane for which the appli-
cation for type certificate was filed on
or after May 1, 1972, must comply with
the material requirements under which
the airplane was type certificated, re-
gardless of passenger capacity, if there
is a substantially complete replace-
ment of the cabin interior on or after
that date.
(3)
Airplane type certificated after Jan-
uary 1, 1958, with passenger capacity of 20
or more
—(i)
Substantially complete re-
placement of the cabin interior on or after
March 6, 1995.
Except as provided in
paragraph (a)(3)(ii) of this section, each
airplane that was type certificated
after January 1, 1958, and has a pas-
senger capacity of 20 or more, must
comply with the heat release rate test-
ing provisions of § 25.853(d) in effect
March 6, 1995 (formerly § 25.853(a–1) in
effect on August 20, 1986)(see app. L of
this part), if there is a substantially
complete replacement of the cabin in-
terior components identified in
§ 25.853(d), on or after that date, except
that the total heat release over the
first 2 minutes of sample exposure shall
not exceed 100 kilowatt-minutes per
square meter and the peak heat release
rate must not exceed 100 kilowatts per
square meter.
(ii)
Substantially complete replacement
of the cabin interior on or after August 20,
1990.
Each airplane that was type cer-
tificated after January 1, 1958, and has
a passenger capacity of 20 or more,
must comply with the heat release rate
and smoke testing provisions of
§ 25.853(d) in effect March 6, 1995 (for-
merly § 25.853(a–1) in effect on Sep-
tember 26, 1988)(see app. L of this part),
if there is a substantially complete re-
placement of the cabin interior compo-
nents identified in § 25.853(d), on or
after August 20, 1990.
(4) Contrary provisions of this sec-
tion notwithstanding, the Director of
the division of the Aircraft Certifi-
cation Service responsible for the air-
worthiness rules may authorize devi-
ation from the requirements of para-
graph (a)(1)(i), (a)(1)(ii), (a)(3)(i), or
(a)(3)(ii) of this section for specific
components of the cabin interior that
do not meet applicable flammability
and smoke emission requirements, if
the determination is made that special
circumstances exist that make compli-
ance impractical. Such grants of devi-
ation will be limited to those airplanes
manufactured within 1 year after the
applicable date specified in this section
and those airplanes in which the inte-
rior is replaced within 1 year of that
date. A request for such grant of devi-
ation must include a thorough and ac-
curate analysis of each component sub-
ject to § 25.853(a–1), the steps being
taken to achieve compliance, and, for
the few components for which timely
compliance will not be achieved, cred-
ible reasons for such noncompliance.
(5) Contrary provisions of this sec-
tion notwithstanding, galley carts and
galley standard containers that do not
meet the flammability and smoke
emission requirements of § 25.853(d) in
effect March 6, 1995 (formerly § 25.853(a–
1)) (see app. L of this part) may be used
in airplanes that must meet the re-
quirements of paragraphs (a)(1)(i),
(a)(1)(ii), (a)(3)(i), or (a)(3)(ii) of this
section, provided the galley carts or
standard containers were manufac-
tured prior to March 6, 1995.
(b)
Seat cushions.
Seat cushions, ex-
cept those on flight crewmember seats,
in each compartment occupied by crew
or passengers, must comply with the
127
Federal Aviation Administration, DOT
§ 121.313
requirements pertaining to seat cush-
ions in § 25.853(c) effective on November
26, 1984, on each airplane as follows:
(1) Each transport category airplane
type certificated after January 1, 1958;
and
(2) On or after December 20, 2010,
each nontransport category airplane
type certificated after December 31,
1964.
(c)
All interior materials; airplanes type
certificated in accordance with SFAR No.
41 of 14 CFR part 21.
No person may op-
erate an airplane that conforms to an
amended or supplemental type certifi-
cate issued in accordance with SFAR
No. 41 of 14 CFR part 21 for a maximum
certificated takeoff weight in excess of
12,500 pounds unless the airplane meets
the compartment interior require-
ments set forth in § 25.853(a) in effect
March 6, 1995 (formerly § 25.853(a), (b),
(b–1), (b–2), and (b–3) of this chapter in
effect on September 26, 1978)(see app. L
of this part).
(d)
All interior materials; other air-
planes.
For each material or seat cush-
ion to which a requirement in para-
graphs (a), (b), or (c) of this section
does not apply, the material and seat
cushion in each compartment used by
the crewmembers and passengers must
meet the applicable requirement under
which the airplane was type certifi-
cated.
(e) Thermal/acoustic insulation ma-
terials. For transport category air-
planes type certificated after January
1, 1958:
(1) For airplanes manufactured before
September 2, 2005, when thermal/acous-
tic insulation is installed in the fuse-
lage as replacements after September
2, 2005, the insulation must meet the
flame propagation requirements of
§ 25.856 of this chapter, effective Sep-
tember 2, 2003, if it is:
(i) Of a blanket construction or
(ii) Installed around air ducting.
(2) For airplanes manufactured after
September 2, 2005, thermal/acoustic in-
sulation materials installed in the fu-
selage must meet the flame propaga-
tion requirements of § 25.856 of this
chapter, effective September 2, 2003.
(3) For airplanes with a passenger ca-
pacity of 20 or greater, manufactured
after September 2, 2009, thermal/acous-
tic insulation materials installed in
the lower half of the fuselage must
meet the flame penetration resistance
requirements of § 25.856 of this chapter,
effective September 2, 2003.
[Doc. No. 28154, 60 FR 65930, Dec. 20, 1995, as
amended by Amdt. 121–301, 68 FR 45083, July
31, 2003; Amdt. 121–320, 70 FR 77752, Dec. 30,
2005; Amdt. 121–330, 72 FR 1442, Jan. 12, 2007;
Docket FAA–2018–0119, Amdt. 121–380, 83 FR
9173, Mar. 5, 2018]
§ 121.313 Miscellaneous equipment.
No person may conduct any oper-
ation unless the following equipment is
installed in the airplane:
(a) If protective fuses are installed on
an airplane, the number of spare fuses
approved for that airplane and appro-
priately described in the certificate
holder’s manual.
(b) A windshield wiper or equivalent
for each pilot station.
(c) A power supply and distribution
system that meets the requirements of
§§ 25.1309, 25.1331, 25.1351(a) and (b)(1)
through (4), 25.1353, 25.1355, and
25.1431(b) or that is able to produce and
distribute the load for the required in-
struments and equipment, with use of
an external power supply if any one
power source or component of the
power distribution system fails. The
use of common elements in the system
may be approved if the Administrator
finds that they are designed to be rea-
sonably protected against malfunc-
tioning. Engine-driven sources of en-
ergy, when used, must be on separate
engines.
(d) A means for indicating the ade-
quacy of the power being supplied to
required flight instruments.
(e) Two independent static pressure
systems, vented to the outside atmos-
pheric pressure so that they will be
least affected by air flow variation or
moisture or other foreign matter, and
installed so as to be airtight except for
the vent. When a means is provided for
transferring an instrument from its
primary operating system to an alter-
nate system, the means must include a
positive positioning control and must
be marked to indicate clearly which
system is being used.
(f) A door between the passenger and
pilot compartments (
i.e.
, flightdeck
door), with a locking means to prevent
passengers from opening it without the