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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; 

(2) On or after December 20, 2010, 

each nontransport category airplane 
type certificated after December 31, 


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). 


All interior materials; other air-


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-

(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 

(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 

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