[Code of Federal Regulations] [Title 14, Volume 2] [Revised as of January 1, 2008] From the U.S. Government Printing Office via GPO Access [CITE: 14CFR121.312] [Page 779-781] TITLE 14--AERONAUTICS AND SPACE CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) PART 121_OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS-- Subpart K_Instrument and Equipment Requirements Sec. 121.312 Materials for compartment interiors. (a) All interior materials; transport category airplanes and nontransport category airplanes type certificated before January 1, 1965. Except for the materials covered by paragraph (b) of this section, all materials in each compartment of a transport category airplane, or a nontransport category airplane type certificated before January 1, 1965, used by the crewmembers and passengers, must meet the requirements of Sec. 25.853 of this chapter in effect as follows, or later amendment thereto: (1) Airplane with passenger seating capacity of 20 or more--(i) Manufactured after August 19, 1988, but prior to August 20, 1990. Except as provided in paragraph (a)(3)(ii) 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 comply with the heat release rate testing provisions of Sec. 25.853(d) in effect March 6, 1995 (formerly Sec. 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 sample exposure must not exceed 100 kilowatt minutes per square meter and the peak heat release rate must not exceed 100 kilowatts per square meter. (ii) Manufactured after August 19, 1990. Each airplane with a passenger capacity of 20 or more and manufactured [[Page 780]] after August 19, 1990, must comply with the heat release rate and smoke testing provisions of Sec. 25.853(d) in effect March 6, 1995 (formerly Sec. 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 application for type certificate was filed prior to May 1, 1972. Except as provided in paragraph (a)(3)(i) or (a)(3)(ii) of this section, each airplane for which the application for type certificate was filed prior to May 1, 1972, must comply with the provisions of Sec. 25.853 in effect on April 30, 1972, regardless of passenger capacity, if there is a substantially complete replacement of the cabin interior 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 paragraph (a)(3)(i) or (a)(3)(ii) of this section, each airplane for which the application for type certificate was filed on or after May 1, 1972, must comply with the material requirements under which the airplane was type certificated, regardless of passenger capacity, if there is a substantially complete replacement of the cabin interior on or after that date. (3) Airplane type certificated after January 1, 1958, with passenger capacity of 20 or more--(i) Substantially complete replacement 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 passenger capacity of 20 or more, must comply with the heat release rate testing provisions of Sec. 25.853(d) in effect March 6, 1995 (formerly Sec. 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 interior components identified in Sec. 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 certificated 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 Sec. 25.853(d) in effect March 6, 1995 (formerly Sec. 25.853(a-1) in effect on September 26, 1988)(see app. L of this part), if there is a substantially complete replacement of the cabin interior components identified in Sec. 25.853(d), on or after August 20, 1990. (4) Contrary provisions of this section notwithstanding, the Manager of the Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, may authorize deviation from the requirements of paragraph (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 compliance impractical. Such grants of deviation will be limited to those airplanes manufactured within 1 year after the applicable date specified in this section and those airplanes in which the interior is replaced within 1 year of that date. A request for such grant of deviation must include a thorough and accurate analysis of each component subject to Sec. 25.853(a-1), the steps being taken to achieve compliance, and, for the few components for which timely compliance will not be achieved, credible reasons for such noncompliance. (5) Contrary provisions of this section notwithstanding, galley carts and galley standard containers that do not meet the flammability and smoke emission requirements of Sec. 25.853(d) in effect March 6, 1995 (formerly Sec. 25.853(a-1)) (see app. L of this part) may be used in airplanes that must meet the requirements 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 manufactured prior to March 6, 1995. (b) Seat cushions. Seat cushions, except those on flight crewmember seats, in each compartment occupied by crew or passengers, must comply with the requirements pertaining to seat cushions in Sec. 25.853(c) effective on November 26, 1984, on each airplane as follows: [[Page 781]] (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 operate an airplane that conforms to an amended or supplemental type certificate 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 requirements set forth in Sec. 25.853(a) in effect March 6, 1995 (formerly Sec. 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 airplanes. For each material or seat cushion to which a requirement in paragraphs (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 certificated. (e) Thermal/acoustic insulation materials. For transport category airplanes type certificated after January 1, 1958: (1) For airplanes manufactured before September 2, 2005, when thermal/acoustic insulation is installed in the fuselage as replacements after September 2, 2005, the insulation must meet the flame propagation requirements of Sec. 25.856 of this chapter, effective September 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 insulation materials installed in the fuselage must meet the flame propagation requirements of Sec. 25.856 of this chapter, effective September 2, 2003. (3) For airplanes with a passenger capacity of 20 or greater, manufactured after September 2, 2009, thermal/acoustic insulation materials installed in the lower half of the fuselage must meet the flame penetration resistance requirements of Sec. 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]