460 

14 CFR Ch. I (1–1–24 Edition) 

§ 135.169 

Records Administration (NARA). For 
information on the availability of this 
material at NARA, call (202) 741–6030 or 
go to 

http://www.archives.gov/fed-

eral

_

register/code

_

of

_

federal

_

regulations/ 

ibr

_

locations.html. 

(1) U.S. Department of Transpor-

tation, Subsequent Distribution Office, 
DOT Warehouse M30, Ardmore East 
Business Center, 3341 Q 75th Avenue, 
Landover, MD 20785; telephone (301) 
322–5377. Copies are also available on 
the FAA’s Web site. Use the following 
link and type the TSO number in the 
search box: 

http://www.airweb.faa.gov/

Regulatory

_

and

_

Guidance

_

Library/

rgTSO.nsf/Frameset?OpenPage. 

(i) TSO–C126, 406 MHz Emergency Lo-

cator Transmitter (ELT), Dec. 23, 1992, 

(ii) TSO–C126a, 406 MHz Emergency 

Locator Transmitter (ELT), Dec. 17, 
2008, and 

(iii) TSO–C126b, 406 MHz Emergency 

Locator Transmitter (ELT), Nov. 26, 
2012. 

(2) RTCA, Inc., 1150 18th Street NW., 

Suite 910, Washington, DC 20036, tele-
phone (202) 833–9339, and are also avail-
able on RTCA’s Web site at 

http:// 

www.rtca.org/onlinecart/index.cfm. 

(i) RTCA DO–204, Minimum Oper-

ational Performance Standards 
(MOPS) 406 MHz Emergency Locator 
Transmitters (ELTs), Sept. 29, 1989, and 

(ii) RTCA DO–204A, Minimum Oper-

ational Performance Standards 
(MOPS) 406 MHz Emergency Locator 
Transmitters (ELT), Dec. 6, 2007. 

[Doc. No. FAA–2010–0982, 79 FR 9973, Feb. 21, 
2014, as amended by Amdt. 135–138, 83 FR 
1189, Jan. 10, 2018] 

§ 135.169 Additional airworthiness re-

quirements. 

(a) Except for commuter category 

airplanes, no person may operate a 
large airplane unless it meets the addi-
tional airworthiness requirements of 
§§ 121.213 through 121.283 and 121.307 of 
this chapter. 

(b) No person may operate a small 

airplane that has a passenger-seating 
configuration, excluding pilot seats, of 
10 seats or more unless it is type cer-
tificated— 

(1) In the transport category; 
(2) Before July 1, 1970, in the normal 

category and meets special conditions 
issued by the Administrator for air-

planes intended for use in operations 
under this part; 

(3) Before July 19, 1970, in the normal 

category and meets the additional air-
worthiness standards in Special Fed-
eral Aviation Regulation No. 23; 

(4) In the normal category and meets 

the additional airworthiness standards 
in appendix A; 

(5) In the normal category and com-

plies with section 1.(a) of Special Fed-
eral Aviation Regulation No. 41; 

(6) In the normal category and com-

plies with section 1.(b) of Special Fed-
eral Aviation Regulation No. 41; 

(7) In the commuter category; or 
(8) In the normal category, as a 

multi-engine certification level 4 air-
plane as defined in part 23 of this chap-
ter. 

(c) No person may operate a small 

airplane with a passenger seating con-
figuration, excluding any pilot seat, of 
10 seats or more, with a seating con-
figuration greater than the maximum 
seating configuration used in that type 
airplane in operations under this part 
before August 19, 1977. This paragraph 
does not apply to— 

(1) An airplane that is type certifi-

cated in the transport category; or 

(2) An airplane that complies with— 
(i) Appendix A of this part provided 

that its passenger seating configura-
tion, excluding pilot seats, does not ex-
ceed 19 seats; or 

(ii) Special Federal Aviation Regula-

tion No. 41. 

(d) Cargo or baggage compartments: 
(1) After March 20, 1991, each Class C 

or D compartment, as defined in § 25.857 
of part 25 of this chapter, greater than 
200 cubic feet in volume in a transport 
category airplane type certificated 
after January 1, 1958, must have ceiling 
and sidewall panels which are con-
structed of: 

(i) Glass fiber reinforced resin; 
(ii) Materials which meet the test re-

quirements of part 25, appendix F, part 
III of this chapter; or 

(iii) In the case of liner installations 

approved prior to March 20, 1989, alu-
minum. 

(2) For compliance with this para-

graph, the term ‘‘liner’’ includes any 

461 

Federal Aviation Administration, DOT 

§ 135.170 

design feature, such as a joint or fas-
tener, which would affect the capa-
bility of the liner to safely contain a 
fire. 

[Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as 
amended by Amdt. 135–2, 44 FR 53731, Sept. 
17, 1979; Amdt. 135–21, 52 FR 1836, Jan. 15, 
1987; 52 FR 34745, Sept. 14, 1987; Amdt. 135–31, 
54 FR 7389, Feb. 17, 1989; Amdt. 135–55, 60 FR 
6628, Feb. 2, 1995; Docket FAA–2015–1621, 
Amdt. 135–136, 81 FR 96701, Dec. 30, 2016] 

§ 135.170 Materials for compartment 

interiors. 

(a) No person may operate an air-

plane that conforms to an amended or 
supplemental type certificate issued in 
accordance with SFAR No. 41 for a 
maximum certificated takeoff weight 
in excess of 12,500 pounds unless within 
one year after issuance of the initial 
airworthiness certificate under that 
SFAR, the airplane meets the compart-
ment interior requirements set forth in 
§ 25.853(a) in effect March 6, 1995 (for-
merly § 25.853 (a), (b), (b–1), (b–2), and 
(b–3) of this chapter in effect on Sep-
tember 26, 1978). 

(b) Except for commuter category 

airplanes and airplanes certificated 
under Special Federal Aviation Regula-
tion No. 41, no person may operate a 
large airplane unless it meets the fol-
lowing additional airworthiness re-
quirements: 

(1) Except for those materials cov-

ered by paragraph (b)(2) of this section, 
all materials in each compartment 
used by the crewmembers or passengers 
must meet the requirements of § 25.853 
of this chapter in effect as follows or 
later amendment thereto: 

(i) Except as provided in paragraph 

(b)(1)(iv) of this section, each airplane 
with a passenger capacity of 20 or more 
and manufactured after August 19, 1988, 
but prior to August 20, 1990, must com-
ply 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), except that the 
total heat release over the first 2 min-
utes of sample exposure rate must not 
exceed 100 kilowatt minutes per square 
meter and the peak heat release rate 
must not exceed 100 kilowatts per 
square meter. 

(ii) Each airplane with a passenger 

capacity of 20 or more and manufac-

tured after August 19, 1990, must com-
ply with the heat release rate and 
smoke testing provisions of § 25.853(d) 
in effect March 6, 1995 (formerly 
§ 25.83(a–1) in effect on September 26, 
1988). 

(iii) Except as provided in paragraph 

(b)(1) (v) or (vi) of this section, each 
airplane for which the application for 
type certificate was filed prior to May 
1, 1972, must comply with the provi-
sions of § 25.853 in effect on April 30, 
1972, regardless of the passenger capac-
ity, if there is a substantially complete 
replacement of the cabin interior after 
April 30, 1972. 

(iv) Except as provided in paragraph 

(b)(1) (v) or (vi) of this section, each 
airplane for which the application for 
type certificate was filed after May 1, 
1972, must comply with the material 
requirements under which the airplane 
was type certificated regardless of the 
passenger capacity if there is a sub-
stantially complete replacement of the 
cabin interior after that date. 

(v) Except as provided in paragraph 

(b)(1)(vi) of this section, each airplane 
that was type certificated after Janu-
ary 1, 1958, must comply with the heat 
release testing provisions of § 25.853(d) 
in effect March 6, 1995 (formerly 
§ 25.853(a–1) in effect on August 20, 1986), 
if there is a substantially complete re-
placement of the cabin interior compo-
nents identified in that paragraph 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 shall not ex-
ceed 100 kilowatts per square meter. 

(vi) Each airplane that was type cer-

tificated after January 1, 1958, 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) in effect on August 20, 1986), 
if there is a substantially complete re-
placement of the cabin interior compo-
nents identified in that paragraph after 
August 19, 1990. 

(vii) 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 (b)(1)(i), (b)(1)(ii), (b)(1)(v), or