Appendix F
Part I – Test Criteria and Procedures for Showing Compliance with JAR 25.853, or 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 nondecorative
coated fabrics, leather, trays
and galley furnishings, electrical conduit,
thermal and acoustical insulation and
insulation covering, air ducting, joint and
edge covering, liners of Class B and E
cargo or baggage compartments, floor
panels of Class B, C, D, or E cargo or
baggage compartments, insulation
blankets, cargo covers and transparencies,
moulded and thermoformed
parts, air ducting joints, and trim strips
(decorative and chafing), that are
constructed of materials not covered in
sub-paragraph (iv) below, must be selfextinguishing
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
(203·2 mm), 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
(63·5 mm) 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) Thermal and acoustic
insulation (including coverings) used in
each cargo and baggage compartment
must be constructed of materials that
meet the requirements set forth in subparagraph
(a)(1)(ii) of Part I of this
Appendix.
(ii) A cargo or baggage
compartment defined in JAR 25.857 as
Class B or E must have a liner
constructed of materials that meet the
requirements of sub-paragraph (a)(1)(ii)
of Part I of this Appendix and separated
from the aeroplane 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
Appendix F
Part I – Test Criteria and Procedures for Showing Compliance with JAR 25.853, or 25.855
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 JAR 25.857 as
Class B, C, D, or E must have floor
panels constructed of materials which
meet the requirements of sub-paragraph
(a)(1)(ii) of Part I of this Appendix and
which are separated from the aeroplane
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
sub-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
sub-paragraph (a)(1)(v) of Part I of this
Appendix.
(3) Electrical system components.
Insulation on electrical wire or cable installed
in any area of the fuselage must be selfextinguishing
when subjected to the 60 degree
test specified in Part I of this Appendix. The
average burn length may not exceed 3 inches,
(76·2 mm) and the average flame time after
removal of the flame source may not exceed
30 seconds. Drippings from the test specimen
may not continue to flame for more than an
average of 3 seconds after falling.
(b) Test Procedures –
(1) Conditioning. Specimens must be
conditioned to 70 ± 5°F (21·11 ± 3°C), and at
50% ± 5% relative humidity until moisture
equilibrium is reached or for 24 hours. Each
specimen must remain in the conditioning
environment until it is subjected to the flame.
(2) Specimen configuration. Except for
small parts and electrical wire and cable
insulation, materials must be tested either as a
section cut from a fabricated part as installed in
the aeroplane or as a specimen simulating a cut
section, such as a specimen cut from a flat
sheet of the material or a model of the
fabricated part. The specimen may be cut from
any location in a fabricated part; however,
fabricated units, such as sandwich panels, may
not be separated for test. Except as noted
below, the specimen thickness must be no
thicker than the minimum thickness to be
qualified for use in the aeroplane. Test
specimens of thick foam parts, such as seat
cushions, must be ½-inch (12·7 mm) in
thickness. Test specimens of materials that
must meet the requirements of sub-paragraph
(a)(1)(v) of Part I of this Appendix must be no
more than é_LQFK __Â___ mm) in thickness.
Electrical wire and cable specimens must be
the same size as used in the aeroplane. In the
case of fabrics, both the warp and fill direction
of the weave must be tested to determine the
most critical flammability condition.
Specimens must be mounted in a metal frame
so that the two long edges and the upper edge
are held securely during the vertical test
prescribed in sub-paragraph (4) of this
paragraph and the two long edges and the edge
away from the flame are held securely during
the horizontal test prescribed in sub-paragraph
(5) of this paragraph. The exposed area of the
specimen must be at least 2 inches (50·8 mm)
wide and 12 inches (304·8 mm) long, unless
the actual size used in the aeroplane is smaller.
The edge to which the burner flame is applied
must not consist of the finished or protected
edge of the specimen but must be
representative of the actual cross-section of the
material or part as installed in the aeroplane.
The specimen must be mounted in a metal
frame so that all four edges are held securely
and the exposed area of the specimen is at least
8 inches by 8 inches (203·2 mm by 203·2 mm)
during the 45° test prescribed in sub-paragraph
(6) of this paragraph.
(3) Apparatus. Except as provided in
sub-paragraph (7) of this paragraph, tests must
be conducted in a draught-free cabinet in
accordance with Federal Test Method Standard
191 Model 5903 (revised Method 5902) for the
vertical test, or Method 5906 for horizontal test
(available from the General Services
Administration, Business Service Centre,
Region 3, Seventh & D Streets SW.,
Washington, DC 20407). Specimens which are
too large for the cabinet must be tested in
similar draught-free conditions.
(4) Vertical test. A minimum of three
specimens must be tested and results averaged.
For fabrics, the direction of weave
corresponding to the most critical flammability
conditions must be parallel to the longest
dimension. Each specimen must be supported
vertically. The specimen must be exposed to a
Bunsen or Tirril burner with a nominal ê_LQFK
(9·525 mm) I.D. tube adjusted to give a flame
of 1½ inches (38·1 mm) in height. The
minimum flame temperature measured by a
calibrated thermocouple pyrometer in the
centre of the flame must be 1550°F (843·33°C).
The lower edge of the specimen must be
¾-inch (19·05 mm) above the top edge of the
burner. The flame must be applied to the
centre line of the lower edge of the specimen.
For materials covered by sub-paragraph
(a)(1)(i) of Part I of this Appendix, the flame
must be applied for 60 seconds and then
removed. For materials covered by subparagraph
(a)(1)(ii) of Part I of this Appendix,
the flame must be applied for 12 seconds and
then removed. Flame time, burn length, and
flaming time of drippings, if any, may be
recorded. The burn length determined in
accordance with sub-paragraph (7) of this
paragraph must be measured to the nearest
tenth of an inch (2·54 mm).
(5) Horizontal test. A minimum of
three specimens must be tested and the results
averaged. Each specimen must be supported
horizontally. The exposed surface, when
installed in the aircraft, must be face down for
the test. The specimen must be exposed to a
Bunsen or Tirrill burner with a nominal ê_LQFK
(9·525 mm) I.D. tube adjusted to give a flame
of 1½ inches (38·1 mm) in height. The
minimum flame temperature measured by a
calibrated thermocouple pyrometer in the
centre of the flame must be 1550°F (843·33°C).
The specimen must be positioned so that the
edge being tested is centred ¾-inch (19·05 mm)
above the top of the burner. The flame must be
applied for 15 seconds and then removed. A
minimum of 10 inches (254 mm) of specimen
must be used for timing purposes,
approximately 1½ inches (38·1 mm) must burn
before the burning front reaches the timing
zone, and the average burn rate must be
recorded.
(6) Forty-five degree test. A minimum
of three specimens must be tested and the
results averaged. The specimens must be
supported at an angle of 45° to a horizontal
surface. The exposed surface when installed in
the aircraft must be face down for the test. The
specimens must be exposed to a Bunsen or
Tirrill burner with a nominal ê_LQFK
(9·525 mm) I.D. tube adjusted to give a flame
of 1½ inches (38·1 mm) in height. The
minimum flame temperature measured by a
calibrated thermocouple pyrometer in the
centre of the flame must be 1550°F (843·33°C).
Suitable precautions must be taken to avoid
draughts. The flame must be applied for
30 seconds with one-third contacting the
material at the centre of the specimen and then
removed. Flame time, glow time, and whether
the flame penetrates (passes through) the
specimen must be recorded.
(7) Sixty degree test. A minimum of
three specimens of each wire specification
(make and size) must be tested. The specimen
of wire or cable (including insulation) must be
placed at an angle of 60° with the horizontal in
the cabinet specified in sub-paragraph (3) of
this paragraph with the cabinet door open
during the test, or must be placed within a
chamber approximately 2 feet (609·6 mm) high
by 1 foot by 1 foot (304·8 mm by 304·8 mm),
open at the top and at one vertical side (front),
and which allows sufficient flow of air for
complete combustion, but which is free from
draughts. The specimen must be parallel to
and approximately 6 inches (152·4 mm) from
the front of the chamber. The lower end of the
specimen must be held rigidly clamped. The
upper end of the specimen must pass over a
pulley or rod and must have an appropriate
weight attached to it so that the specimen is
held tautly throughout the flammability test.
The test specimen span between lower clamp
and upper pulley or rod must be 24 inches
(609·6 mm) and must be marked 8 inches
(203·2 mm) from the lower end to indicate the
central point for flame application. A flame
from a Bunsen or Tirrill burner must be applied
for 30 seconds at the test mark. The burner
must be mounted underneath the test mark on
the specimen, perpendicular to the specimen
and at an angle of 30° to the vertical plane of
the specimen. The burner must have a nominal
bore of ê_LQFK (9·525 mm) and be adjusted to
provide a 3-inch (76·2 mm) high flame with an
inner cone approximately one-third of the
flame height. The minimum temperature of the
hottest portion of the flame, as measured with a
calibrated thermocouple pyrometer, may not be
less than 1750°F (954·44°C). The burner must
be positioned so that the hottest portion of the
flame is applied to the test mark on the wire.
Flame time, burn length, and flaming time of
drippings, if any, must be recorded. The burn
length determined in accordance with subparagraph
(8) of this paragraph must be
measured to the nearest tenth of an inch
(2·54 mm). Breaking of the wire specimens is
not considered a failure.
(8) Burn length. Burn length is the
distance from the original edge to the farthest
evidence of damage to the test specimen due to
flame impingement, including areas of partial
or complete consumption, charring, or
embrittlement, but not including areas sooted,
stained, warped, or discoloured, nor areas
where material has shrunk or melted away from
the heat source.
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