Federal Aviation Administration, DOT

Pt. 25, App. F

(c) Allowances must be made for such time
delays in the execution of the procedures as
may be reasonably expected to occur during
service.
(7) Installation and operation; standby power.
The standby power unit and its installation
must comply with paragraphs (a) and (b) of
this section.
(a) The standby power unit and its installation must not adversely affect the safety of
the airplane.
(b) The operation of the standby power
unit and its control must have proven to be
safe and reliable.
[Amdt. 25-6, 30 FR 8468, July 2, 1965]

APPENDIX F TO PART 25

spaschal on DSK3GDR082PROD with CFR

Part I - Test Criteria and Procedures for
Showing Compliance With Section 25.853 or Section 25.855
(a) Material test criteria - (1) Interior compartments occupied by crew or passengers. (i)
Interior ceiling panels, interior wall panels,
partitions, galley structure, large cabinet
walls, structural flooring, and materials used
in the construction of stowage compartments (other than underseat stowage compartments and compartments for stowing
small items such as magazines and maps)
must be self-extinguishing when tested
vertically in accordance with the applicable
portions of part I of this appendix. The average burn length may not exceed 6 inches and
the average flame time after removal of the
flame source may not exceed 15 seconds.
Drippings from the test specimen may not
continue to flame for more than an average
of 3 seconds after falling.
(ii) Floor covering, textiles (including
draperies and upholstery), seat cushions,
padding, decorative and non-decorative coated fabrics, leather, trays and galley furnishings, electrical conduit, air ducting,
joint and edge covering, liners of Class B and
E cargo or baggage compartments, floor panels of Class B, C, E, or F cargo or baggage
compartments, cargo covers and transparencies, molded and thermoformed parts,
air ducting joints, and trim strips (decorative and chafing), that are constructed of
materials not covered in paragraph (a)(1)(iv)
below, must be self-extinguishing when tested vertically in accordance with the applicable portions of part I of this appendix or
other approved equivalent means. The average burn length may not exceed 8 inches, and
the average flame time after removal of the
flame source may not exceed 15 seconds.
Drippings from the test specimen may not
continue to flame for more than an average
of 5 seconds after falling.
(iii) Motion picture film must be safety
film meeting the Standard Specifications for
Safety Photographic Film PHI.25 (available
from the American National Standards Institute, 1430 Broadway, New York, NY 10018). If

the film travels through ducts, the ducts
must meet the requirements of subparagraph
(ii) of this paragraph.
(iv) Clear plastic windows and signs, parts
constructed in whole or in part of elastomeric materials, edge lighted instrument
assemblies consisting of two or more instruments in a common housing, seat belts,
shoulder harnesses, and cargo and baggage
tiedown equipment, including containers,
bins, pallets, etc., used in passenger or crew
compartments, may not have an average
burn rate greater than 2.5 inches per minute
when tested horizontally in accordance with
the applicable portions of this appendix.
(v) Except for small parts (such as knobs,
handles, rollers, fasteners, clips, grommets,
rub strips, pulleys, and small electrical
parts) that would not contribute significantly to the propagation of a fire and for
electrical wire and cable insulation, materials in items not specified in paragraphs
(a)(1)(i), (ii), (iii), or (iv) of part I of this appendix may not have a burn rate greater
than 4.0 inches per minute when tested horizontally in accordance with the applicable
portions of this appendix.
(2) Cargo and baggage compartments not occupied by crew or passengers.
(i) [Reserved]
(ii) A cargo or baggage compartment defined in Section 25.857 as Class B or E must have a
liner constructed of materials that meet the
requirements of paragraph (a)(1)(ii) of part I
of this appendix and separated from the airplane structure (except for attachments). In
addition, such liners must be subjected to
the 45 degree angle test. The flame may not
penetrate (pass through) the material during
application of the flame or subsequent to its
removal. The average flame time after removal of the flame source may not exceed 15
seconds, and the average glow time may not
exceed 10 seconds.
(iii) A cargo or baggage compartment defined in Section 25.857 as Class B, C, E, or F must
have floor panels constructed of materials
which meet the requirements of paragraph
(a)(1)(ii) of part I of this appendix and which
are separated from the airplane structure
(except for attachments). Such panels must
be subjected to the 45 degree angle test. The
flame may not penetrate (pass through) the
material during application of the flame or
subsequent to its removal. The average
flame time after removal of the flame source
may not exceed 15 seconds, and the average
glow time may not exceed 10 seconds.
(iv) Insulation blankets and covers used to
protect cargo must be constructed of materials that meet the requirements of paragraph (a)(1)(ii) of part I of this appendix. Tiedown equipment (including containers, bins,
and pallets) used in each cargo and baggage
compartment must be constructed of materials that meet the requirements of paragraph (a)(1)(v) of part I of this appendix.

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