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Appendix 1 to ETSO-C69c - Federal Aviation Administration Minimum Performance Standard for Emergency Evacuation Slides, Ramps, Ramp/Slides, and Slide/Rafts

Available versions for ERULES-1963177438-7134

ED Decision 2003/10/RM found in: CS-ETSO Amdt 17 - European Technical Standard Orders (Oct 2026)

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###### Appendix 1 to ETSO-C69c – Federal Aviation Administration Minimum Performance Standard for Emergency Evacuation Slides, Ramps, Ramp/Slides, and Slide/Rafts

*ED
Decision
2003/10/RM*

**Note:
Any reference made to US standards, regulations and organisations are
for information purpose only and may be replaced, if applicable, by
the European equivalent when acceptable to the Agency.**

1. Purpose. This standard provides the minimum performance standards
for inflatable emergency evacuation slides, overwing exit ramps,
ramp/slides, and slide/rafts. However, the deployment and erection
characteristics for these devices, as installed on the aircraft, are
specified in Title 14 of the Code of Federal Regulations (14 CFR) §
25.810 and must be complied with along with the requirements in this
TSO.

2. Scope. This performance standard provides for the following types
of emergency evacuation devices:

Type I - Inflatable slide suitable for assisting occupants in
descending from a floor-level aircraft exit or from an aircraft wing.

Type II - Inflatable slide also designed to be used as a life raft,
i.e. a slide/raft.

Type III - Inflatable exit ramp suitable for assisting occupants in
descending to an aircraft wing from certain overwing exits.

Type IV - Combination inflatable exit ramp and wing-to-ground slide.

Further definitions of terms used in this TSO are given in [appendix
2](#_DxCrossRefBm920220755).

3. Materials. The materials used must be of a quality, which
experience and/or tests have demonstrated to be suitable for use in
emergency evacuation slides, ramps, ramp/slides and slide/rafts, i.e.
emergency evacuation devices.

3.1 Nonmetallic Materials.

3.1.1 The finished device must be clean and free from any defects
that might affect its function.

3.1.2 Coated fabrics and other items, such as webbing, which are
subject to deterioration must have been manufactured not more than 18
months prior to the date of manufacture of the finished product.
However, these materials may be re-qualified for an additional 18
months if they pass the requirements of paragraph 5.1 of this
appendix.

3.1.3 The materials must not support fungus growth.

3.1.4 Materials used in the construction of flotation chambers and
decks for Type II devices must be capable of withstanding the
detrimental effects of exposure to fuels, oils, hydraulic fluids, and
sea water.

3.1.5 Coated Fabric. Coated fabrics, including seams, which are
subject to deterioration and used in the manufacture of the devices,
must retain at least 90 percent of their original physical properties
after these fabrics have been subjected to the accelerated aging test
specified in paragraph 5.1 of this appendix.

3.1.5.1 Strength. Coated fabrics used for these applications must
conform to the following minimum strengths after aging:

Tensile Strength (Grab Test)

Warp 190 pounds/inch

Fill 190 pounds/inch

Tear Strength (Trapezoid Test or Tongue Test)

Non walking/sliding surface:
13 x 13 pounds/inch (minimum)

Walking/Sliding surface: 50 x
50 pounds/inch (minimum)

Puncture Strength

Walking/Sliding surface: 67
pounds force

3.1.5.2 Adhesion. In addition to the strength requirements of
paragraph 3.1.5.1 above, coated fabrics must meet the following
minimum strengths after aging:

Ply Adhesion

5 pounds/inch width at 70 + 2
degrees F at a separation rate of 2.0 to 2.5 inches/minute

Coat Adhesion

5 pounds/inch width at 70 + 2
degrees F at a separation rate of 2.0 to 2.5 inches/minute

3.1.5.3 Permeability. For coated fabrics used in the manufacture of
inflation chambers, the maximum permeability to helium may not exceed
10 liters per square meter in 24 hours at 77 degrees F, or its
equivalent using hydrogen, using either of the permeability test
methods specified in paragraph 5.1 of this appendix. The permeameter
must be calibrated for the gas used. In lieu of either of these
permeability tests, an alternate test may be used provided the
alternate test has been approved as an equivalent to this
permeability test by the manager of the FAA office having purview of
the manufacturer's facilities, as required in paragraphs 3b,
Deviations and 5a, Application Data, of this TSO.

3.1.5.4 Hydrolysis. Pressure holding coated fabrics, including seams,
must be shown to be resistant to hydrolysis. It must be shown by
tests specified in paragraph 5.1 of this appendix that the porosity
of the basic pressure holding material is not increased as a result
of the material being subjected to hydrolysis conditioning. Seam
strength and coat adhesion must not be reduced more than 20 percent
and still must not fall below the minimums prescribed in paragraphs
3.1.5.2 and 3.1.6 of this appendix as a result of hydrolysis
conditioning.

3.1.6 Seam Strength and Adhesives. Seams used in the manufacture of
the device must meet the following minimum strength requirements:

Shear Strength (Grab Test)

175 pounds/inch width at 75
degrees F

40 pounds/inch width at 140
degrees F

Peel Strength (Peel Test)

5 pounds/inch width at 70
degrees F

3.1.7 Seam Tape. If tape is used for seam reinforcement or abrasion
protection of seams or both, the fabric used for the seam tape must
have a minimum breaking strength (Grab Test) of 40 pounds/inch width
in both the warp and fill directions. When applied to the seam area,
the adhesion strength characteristics must meet the seam strength
requirements in paragraph 3.1.6 above.

3.1.8 Canopy. Fabrics used for this purpose on Type II slide/rafts
must be waterproof and resistant to sun penetration, must not affect
the potability of collected water, and must meet the following
minimum requirements in the applicable tests prescribed in paragraph
5.1 of this appendix, except that in lieu of meeting the tensile
strength requirements, a fabricated canopy erected on the device may
be demonstrated to withstand sustained wind velocities of 35 knots
and 52-knot gusts:

Tensile Strength (Grab Test)

Warp 75 pounds/inch

Fill 75 pounds/inch

Tear Strength (Tongue or Trapezoid Test)

4 x 4 pounds/inch

Coat Adhesion of Coated Fabrics

3.5 pounds/inch width at 70±2
degrees F at a separation rate of 2.0 to 2.5 inches/minute

3.1.9 Flammability. The device (including carrying case or stowage
container) must be constructed of materials which comply with the
requirements of 14 CFR § 25.853(a), Appendix F, part I (a)(1)(ii) in
effect on March 6, 1995.

3.1.10 Radiant Heat Resistance. The pressure holding materials in the
device must meet the 90-second minimum time to failure requirement
and the 180-second average time to failure requirement of the radiant
heat resistance test specified in paragraph 5.3 of this appendix.

3.1.11 Molded Nonmetallic Fittings. Molded nonmetallic fittings must
retain their physical characteristics when subjected to temperatures
of -65 to +160 degrees F.

3.2 Metallic Parts. All metallic parts must be made of
corrosion-resistant material or must be suitably protected against
corrosion.

3.3 Protection. All inflation chambers and load carrying fabrics must
be protected in such manner that non-fabric parts do not cause
chafing or abrasion of the material in either the packed or the
inflated condition.

4. Detail Requirements.

4.1 Operation. The operation of the device must be simple enough so
that brief, easily understood, posted instructions can be followed by
the user.

4.2 Function. The device, including its inflation system, must be
demonstrated to be capable of fully functioning when subjected to
temperatures from -40 to +160 degrees F. If the device is intended
for installation outside the pressurized cabin, the device must be
capable of functioning after being stowed at -65 degrees F. The
function of the device must be demonstrated in accordance with the
hot and cold soak test procedures described in paragraph 5.9 of this
appendix.

4.3 Strength.

4.3.1 Beam Strength-Type I, II, & IV Devices. The structural
integrity of the device during and after the dynamic challenge of
multiple sand bag loading of the device (to simulate loading by
three, tightly-bunched evacuees entering each lane of the device)
must be shown by test to be adequate, as described in paragraph 5.5
of this appendix.

4.3.2 Attachment Means Strength. The means by which the device is
attached to the aircraft, typically the girt, must not fail and must
remain intact and suitably attached to both the aircraft and the
device during and after the severe loading tests simulating normal
evacuation. The device must withstand the static tensile load tests
defined in this appendix in paragraphs 5.6, for girts, or 5.7, for
non-girts, and 5.8, as appropriate, for evacuees inadvertently
entering pontoon areas. Separate girt specimens may be used in the
two tests required in paragraph 5.6 of this appendix.

4.4 Elimination of Static. The device and its fastening must be so
constructed that static electricity will not be generated in
sufficient quantity to cause a spark which would create a hazard if
there is any fuel spillage nearby.

4.5 Damage Resistance and Usage.

4.5.1 The device must be capable of resisting puncture and tear of
the sliding and walking surfaces and supporting structure from
objects normally carried or worn by passengers that could result in
collapse of the device, prevent the device from performing its
intended function, or both.

4.5.2 Type I, II & IV devices must be so constructed as to permit
their use with ground personnel assistance as a noninflatable device
in the event of puncture or tear which may render the device
incapable of holding air and sustaining inflation.

4.5.3 If the device is of a multiple-inflatable compartment
construction, loss of any one of these compartments must not render
the device totally unusable.

4.6 Length. Type I, II & IV devices must be of such length after
full deployment that the lower end is self-supporting on the ground.
The device must provide safe evacuation of occupants to the ground
when the aircraft is on the ground with the landing gear extended and
after collapse of one or more legs of the landing gear.

4.7 Elimination of Encumbrances. Encumbrances which might be grabbed
by evacuees must be kept to a minimum consistent with good design for
maximum operational efficiency.

4.8 Hardware and Attaching Means Strength. All hardware, webbing and
straps used to attach the device to the aircraft and all straps,
grips, and handholds not associated with attachment to the aircraft
must have a strength not less than 1.5 times the highest design load
imposed in showing compliance with the strength requirements of
paragraph 4.3 of this appendix and for Type II devices, in
establishing the rated capacity under paragraph 4.26.1 of this
appendix.

4.9 Use as Re-entry Device. If the device is designed with provisions
for use as a means of re-entering the aircraft, these additional
provisions must not interfere with the use of the device for
evacuation.

4.10 Evacuation Rate.

4.10.1 The device must be shown, by tests conducted under the
conditions described in paragraph 5.4.1 of this appendix, to be
capable of safely accommodating evacuees at a rate of at least 70
evacuees per minute per lane. The evacuees must exit the device
without assistance.

4.10.2 Evacuation capability under the test conditions shown in
paragraph 5.4.3 of this appendix must be demonstrated in order to
confirm the acceptability of the device and it’s and/or the
associated airplane's emergency lighting system for use by evacuees
under dark-of-night conditions. An evacuation rate based upon the
rating of the exit (see paragraph 5.4.3.10 of this appendix) to which
the device will be attached must be achieved. A detailed test plan to
meet these requirements should be submitted at least 60 days prior to
the test to the FAA aircraft certification office having purview of
the manufacturer's facilities. The test plan shall include, but not
be limited to, the test protocol, a description of the test
facilities, a description of the measurement and recording equipment
and procedures, and the safety provisions for protecting test
participants. The test plan must be approved by the manager of that
FAA office prior to conduct of the test.

4.11 Inflation.

4.11.1 The device must be demonstrated to meet the applicable
automatic inflation requirements of 14 CFR § 25.810 (a)(1)(ii), (b),
and/or (d)(4). See paragraph 4.12 below.

4.11.2 The device shall be designed to prevent its inflation out of
proper sequence.

4.11.3 A manual means of actuating inflation must be provided. The
manual means of actuation of the inflation system may be mechanical
or electrical. However, the manual inflation actuating means must be
neither visible nor presented for use until the device has been
deployed. If the means is not an integral part of the device, details
of its connection must be included in the installation limitations
required in paragraph 5a, Application Data.

4.12 Inflation Time.

4.12.1 Type I floor-level exit slides and Type III devices must be
fully erected in 6 seconds after actuation of the inflation controls
has begun.

4.12.2 Type II devices must meet the requirements in paragraph 4.12.1
above and, if there are actions required to convert usage from slide
mode to raft mode, the time required to complete those actions must
not exceed 10 seconds after actuation of the conversion means.

4.12.3 Type IV devices and Type I wing-to-ground slides must be
automatically erected in not more than 10 seconds after actuation of
the inflation controls.

4.13 Device Length Extensions.

4.13.1 The device extension must be capable of being inflated at any
time after inflation of the basic device has been initiated. The time
required to complete extension of the device must not exceed 4
seconds beyond the time required to inflate the basic device.

4.13.2 Inflation of the extension must be initiated by separate
controls from those for the basic device. The controls must be
clearly identified and must be located separately from the manual
inflation actuation controls to minimize the possibility of
inadvertent actuation.

4.13.3 The junction of the basic device and the extension must not
impede evacuation.

4.14 Manual Inflation Actuation Controls.

4.14.1 Inflation controls must be equipped with a rigid cross member
as an actuation handle. The handle must be red in color, marked with
the word "PULL" (or other appropriate instruction) in high
visibility reflective letters at least 1/2-inch high and of a
contrasting color. In addition, there must be a placard with the
words "PULL TO INFLATE" (or other appropriate instruction)
located as close to the handle as possible.

4.14.2 When the inflation actuation controls are exposed for use,
they must be visible to an aircraft occupant, standing at the
doorsill, under the minimum emergency lighting conditions specified
in 14 CFR § 25.812 in effect at the time of application.

4.14.3 Unless a rational analysis is provided to locate them
elsewhere, or if there is no girt attachment, inflation actuation
controls must be on the right side of the girt as seen by an aircraft
occupant looking out of the aircraft door.

4.14.4 Inflation actuation controls must be so designed that the
maximum required pulling force will not pull the deployed device back
into the doorway. The pulling force required must not exceed 30
pounds.

4.14.5 Inflation actuation controls must be constructed so they
cannot trip or entangle evacuees.

4.14.6 When actuated, the manual inflation actuation controls must
function in a manner which will not cause rotation or twist of the
deployed assist means.

4.15 Inflation System.

4.15.1 The inflation system must be connected to the evacuation
device and ready for instant use. The inflation system must minimize
leakage due to backpressure after inflation.

4.15.2 If an air aspirator system is used, the system must be
constructed to prevent the ingestion of small foreign objects or to
prevent failure or malfunction of the system as a result of ingestion
of the small foreign objects.

4.15.3 Components must meet Department of Transportation (DOT)
Specifications 3AA (49 CFR 178.37) or 3HT (49 CFR 178.44) in effect
May 30, 1976, FRP-1 (49 CFR 178.AA) in effect February 1987, CFFC (49
CFR 178) in effect November 1996, or an equivalent specification
approved by the manager of the FAA office having purview of the
manufacturer's facilities, as required in paragraphs 3b, Deviations
and 5a, Application Data of this TSO.

4.15.4 Inflation systems for Type II devices, in addition to meeting
the above requirements of paragraph 4.15 of this appendix, shall be
arranged so that failure of one inflatable chamber or manifold will
not result in loss of gas from the other chamber. The inflation
equipment shall be located so as not to interfere with boarding
operations.

4.16 Multiple Lane Devices.

4.16.1 A multiple lane device must provide space for evacuees sliding
simultaneously in each lane. Each sliding surface, if separated by a
raised divider not considered to be a part of the sliding surface,
must be at least 20 inches wide. The combined width of two sliding
surfaces not separated by a raised divider must be at least 42
inches. The width of a multiple lane device with no raised lane
divider must be sufficient to enable evacuees to jump side-by-side
into each slide lane simultaneously and reach the ground safely.

4.16.2 A multiple lane device must resist adverse twisting or
deflecting when subjected to maximum asymmetrical loading represented
by evacuees traversing each lane of the device individually at the
evacuation rate prescribed in paragraph 4.10 of this appendix. Test
conditions shall be as specified in paragraph 5.4 of this appendix
except that only the normal sill height and nominal pressure shall be
tested.

4.16.3 Where used, a raised divider or center median must be
constructed so as to prevent injury to evacuees and not to throw from
the device evacuees who jumped into it astraddle or partly astraddle
the divider or median. Multiple lane devices, if canted, must provide
for the avoidance of cross-flow effects due to the canting.

4.17 Side Guards. A single or multiple lane inflatable device must be
equipped with side guards or other means to prevent evacuees from
accidentally missing or falling from the device. The means must
provide protection for an evacuee who crosses the aircraft emergency
exit threshold at a horizontal velocity of approximately 6 feet per
second and contacts the device installed at its steepest design
angle.

4.18 Emergency Knife Location. If an emergency knife is provided, it
must be so installed that it cannot injure persons using the
evacuation device in a normal manner. For Type II devices, the knife
must also meet the requirements of paragraph 4.39 of this appendix.

4.19 Device Illumination.

4.19.1 Integral device illumination must be designed so the
illumination means is activated automatically during deployment or
inflation and the level of illumination meets the appropriate
requirements in 14 CFR § 25.812 in effect at the time of
application.

4.19.2 The illumination means must not interfere with the safe
evacuation of persons using the device in a normal manner.

4.20 Wind. The device must be shown, in 25-knot winds directed from
the most critical angle, to deploy and, with the assistance of only
one person who has evacuated down the device, to remain usable after
full deployment to evacuate occupants safely to the ground. The
device shall be tested while it is properly attached to the exit or
location on the airplane on which installation is intended or on an
equivalent mock-up.

4.20.1 To determine the most critical angle, the wind shall be
directed at the device from at least the following directions: aft
along the centerline of the aircraft (0 degrees position) and then
every 45 degrees on the same side of the fuselage as the device is
intended for installation.

4.20.2 If the straight section of the descent portion of the device
forms an angle greater than 10 degrees to a line perpendicular to the
aircraft centerline, the wind shall be applied to the device from
directions perpendicular to both sides (i.e., the edges of the device
parallel to the straight section of the descent portion) and from
every 45 degrees between these two directions on the same side of the
fuselage as the device is intended for installation. For directions
which are not tested, a rational analysis shall be presented to show
why those directions are less critical than those tested.

4.21 Device Surface.

4.21.1 The surfaces of the device, including its coating, must be
suitable and safe for use in any weather condition, including a
rainfall of 1 inch per hour. The evacuation rate achieved in
demonstrating suitability and safety of the device sliding surface
under rainfall conditions shall be no less than that shown in
paragraph 5.4.3.10. Evacuees shall meet the requirements of paragraph
5.4.1.5 of this appendix.

4.21.2 Each device sliding lane, including its coating, must provide
safe and rapid evacuation without detrimental erosion or
deterioration for at least 200 adult persons without any rework of
the surface.

4.22 Device Performance. At least five consecutive deployment and
erection tests must be demonstrated without failure. At least three
tests must be conducted using a single representative sample of the
device.

4.23 Dynamic Pressure Retention Test. The device must maintain
adequate pressure to satisfactorily accomplish its intended function
throughout an emergency evacuation in which:

4.23.1 The device is installed at its critical angle (with respect to
buckling);

4.23.2 The device is inflated by the inflation system designed for
that purpose, the initial pressure of which is at the minimum of its
design range;

4.23.3 The pressure relief valve(s), if installed, is unrestricted;
and

4.23.4 At least 200 persons in no more than 10 separate
demonstrations use each slide lane of the device at an average rate
of not less than one person per second per lane.

4.24 Overpressure Tests. The device must be shown to withstand the
overpressure test requirements of paragraph 5.2.2 of this appendix
without damage.

4.25 Static Pressure Retention Test. The device must be shown to meet
the pressure retention test requirements of paragraph 5.2.1 of this
appendix.

4.26 Raft Capacity-Type II Devices.

4.26.1 Rated Capacity. The rated capacity shall be the usable seating
area on the deck/sliding surface of not less than 3.6 ft2/person.

4.26.2 Overload Capacity. The overload capacity shall be the usable
seating area on the deck/sliding surface of not less than 2.4
ft2/person.

4.26.3 Capacity. Alternate Rating Methods. In lieu of the rated
capacity prescribed in paragraph 4.26.1 above, one of the following
methods may be used:

4.26.3.1 The rated capacity of a Type II device may be determined by
the number of seating spaces which can be accommodated within the
occupiable area exclusive of the perimeter structure (such as
inflation/buoyancy tubes) without overlapping of the occupant seating
spaces. The occupant seating spaces may not be less than the
following size unless an equivalent size has been approved by the
manager of the FAA office having purview of the manufacturer's
facilities.

![](/static/files/file_jytjXw2lpRK/image011.png)

4.26.3.2 The rated capacity also may be determined on the basis of a
controlled pool or fresh water demonstration which includes
conditions prescribed under paragraph 5.2.3 of this appendix and the
following:

4.26.3.2.1 The sitting area on the raft deck may not be less than
3.0 ft2/person.

4.26.3.2.2 At least 30 percent but no more than 50 percent of the
participants must be female.

4.26.3.2.3 Except as provided below, all participants must select
their sitting space without outside placement assistance. A raft
commander, acting in the capacity of a crewmember, may direct
occupant seating to the extent necessary to achieve reasonable weight
distribution within the device.

4.26.3.2.4 All participants must not have practiced, rehearsed, or
have had the demonstration procedures described to them within the
past 6 months.

4.27 Buoyancy.

4.27.1 Type I devices installed at main deck floor level exits shall
be designed to have positive buoyancy when extended so that they can
be used as emergency flotation devices.

4.27.2 Type II devices shall have two independent inflatable
flotation tubes. If either tube is deflated, the other tube and the
device floor shall be capable of supporting the rated and overload
capacities in fresh water.

4.27.2.1 It shall be shown by tests in fresh water that the Type II
device, loaded to rated capacity using an average weight of 170
lbs./person, has a freeboard of at least:

4.27.2.1.1 Twelve inches with both flotation tubes at minimum raft
mode operating pressure; and

4.27.2.1.2 Six inches with the critical flotation tube deflated and
the remaining flotation tube at minimum raft mode operating pressure.
In lieu of meeting the 6-inch freeboard requirement of this
paragraph, the buoyancy provided by the tubes only (disregarding
buoyancy derived from the floor and inflatable floor support) shall
be capable of supporting the rated capacity based on an average
weight of at least 200 lbs./person.

4.27.2.2 It shall be shown by tests in fresh water that the Type II
device loaded to its overload capacity and using an average weight of
170 lbs./person has a measurable freeboard with the critical
flotation tube deflated.

Ballast in the form of sandbags or the equivalent may be used to
achieve the 170-lb weight, provided the appropriate distribution
within the device is maintained.

4.28 Disconnect Means.

4.28.1 Type I devices’ disconnect means must be a readily
apparent, flexible cloth/webbing loop capable of being operated by
untrained persons and covered until ready for use. The method of
disconnecting the device from the aircraft must be conspicuously and
clearly indicated by brief instruction placards.

4.28.2 Type II device release from an aircraft, whether by
automatic or manual means, shall not be restricted by the critical
conditions of: (a) floor sill height above the water, (b) wind
velocity and direction, or (c) occupant load. Devices having aircraft
mounted inflation systems shall have means for quick detachment from
the inflation system so that separation cannot cause loss of raft
buoyancy. Release means shall be a readily apparent flexible
cloth/webbing loop capable of being operated by untrained persons and
covered until ready for use. The method of disconnecting the device
from the aircraft must be conspicuously and clearly indicated by
brief instruction placards.

4.29 Mooring Line.

4.29.1 Type I devices must be equipped with a nonrotting mooring line
so that the deployed device automatically will remain secured to the
aircraft when it is used as an emergency flotation platform. The
mooring line shall not endanger the device, cause the device to spill
occupants if the aircraft sinks, or interfere with the operation of
the device. The mooring line shall have a minimum length of 20 feet
and have a knotted breaking strength of not less than 500 lbs. The
attachment to the evacuation device shall be stronger than the
mooring line. The moored device shall be quickly and easily
disconnected from the aircraft. The mooring release means shall be
readily apparent and operable by untrained evacuees.

4.29.2 Type II devices, in addition to meeting the requirements of
paragraph 4.29.1, shall have a mooring line capable of keeping the
device, loaded to rated capacity, attached to a floating aircraft.
The line may be equipped with a mechanical release linkage. The
breaking strength of the line shall be 500 – 1000 pounds.

4.30 Lifeline. Type I and Type II devices shall be equipped with a
nonrotting lifeline of a size greater than or equal to 3/8-inch
diameter or ½-inch width, .060 minimum thickness and of a color that
contrasts with the device. The lifeline shall be attached along at
least 80 percent of the length of both sides of the device. The
lifeline shall not adversely compromise the use of the device as a
slide. The lifeline and its attachment must be capable of
withstanding a minimum load of 500 lbs. and must not interfere with
the device's inflation.

4.31 Capsize Resistance-Type II Devices. There shall be water pockets
or other means to provide ballast to resist capsizing an empty or
lightly loaded raft.

4.32 Righting-Type II Devices. Unless it is shown that there is no
tendency for the device to become inverted during loading and release
from the aircraft, the slide/raft must comply with the righting tests
specified in paragraph 5.2.3.5 of this appendix.

4.33 Boarding Aids-Type II Devices. Boarding aids shall be provided
at two opposing positions on the raft. Boarding aids shall permit
unassisted entry from the water into the unoccupied raft and shall
not at any time impair either the rigidity or the inflation
characteristics of the raft. Puncturing of inflatable boarding aids
shall not affect the buoyancy of the raft flotation chambers.
Boarding handles and/or stirrups used in conjunction with the
boarding aids shall withstand a pull of 500 pounds. Boarding aids
must be shown to comply with the test requirements of paragraph
5.2.3.6 of this appendix.

4.34 Heaving-Trailing Line-Type II Devices. At least one, floating,
heaving-trailing line, not less than 75 ft in length and at least 250
lbs. strength, shall be located on the main flotation tube near the
sea anchor attachment. The attachment point of the line shall
withstand a pull force of not less than 1.5 times the line rated
strength without damage to the device.

4.35 Canopy-Type II Devices. A canopy shall be packed with or
attached to the device. The erected canopy shall be capable of
withstanding sustained wind velocities of 35 knots and 52-knot gusts
in open water. The canopy shall provide adequate headroom, minimum 1
inch clearance, for the 95th percentile male (seated height) and
shall provide openings 180 degrees apart. Means shall be provided to
make the openings weather tight. If the canopy is not integral with
the raft, it shall be capable of being erected by occupants following
conspicuously posted, simple instructions. It shall be capable of
being erected by one occupant of an otherwise empty raft and by
occupants of a raft filled to rated capacity.

4.36 Color-Type II Devices. Except surfaces which have been treated
for the purpose of reflecting radiant heat, the color of the device
surfaces, including the canopy surface, visible from the air shall be
an International Orange-Yellow or an equivalent high visibility
color.

4.37 Sea Anchor-Type II Devices. A sea anchor, or anchors, or other
equivalent means must be provided to maintain the raft, with rated
capacity and canopy installed, on a substantially constant heading
relative to the wind and must have the ability to reduce the drift to
2 knots when subjected to winds of 17 to 27 knots. Unless analysis
and/or test data substantiating the adequacy of a lower breaking
strength is approved by the manager of the FAA office having purview
of the manufacturer's facilities as required in paragraphs 3b,
Deviations, and 5a, Application Data, the line securing a sea anchor
to the device shall have a breaking strength of 500 pounds or 40
pounds times the rated capacity of the raft, whichever is greater.
The attachment of the line to the raft shall be capable of
withstanding a load of 1.5 times the line-rated strength without
damaging the device. The line shall be at least 25 feet in length and
shall be protected to prevent it from being inadvertently cut by raft
occupants.

4.38 Emergency Inflation Equipment-Type II Devices. A means readily
accessible to occupants of the device shall be provided to manually
inflate the device and maintain the raft mode minimum operating
pressure. The emergency inflation means must have a displacement of
at least 32 cubic inches per full stroke. Manual inflation valves,
with a non-return opening adequate for the size and capacity of the
inflation means, shall be located to permit inflation of all
chambers. The inflation means and valves shall have provisions to
prevent inadvertent removal and loss when either stowed or in use.

4.39 Knife-Type II Devices. A hook-type knife secured by a retaining
line shall be sheathed and attached to the device adjacent to the
point of mooring line attachment. This knife must also meet the
requirements of paragraph 4.18 of this appendix.

4.40 Placards- Type II Devices. Suitable placards shall be provided
in contrasting colors in waterproof paint which is not detrimental to
the fabric, that denote use and location of the inflation systems,
raft equipment, boarding aids, and righting aids. The letters used
for such placarding shall be at least 2 inches high, except the
details and miscellaneous instructions may be of smaller lettering.
Applicable placarding shall take into account persons boarding or
righting the raft from the water.

4.41 Emergency Lights-Type II Devices. At least one TSO-C85a, or the
latest revision, approved survivor locator light shall be provided.
The light shall be automatically activated upon device inflation in
the water and shall be visible from any direction by persons in the
water. The light shall be located at or near a boarding station.

4.42 Actuation Means-Type II Devices. If the device as a slide
requires an additional operation to make it usable as a raft, the
means for initiating the additional operation shall be designed to
preclude inadvertent actuation but be readily available for use. If a
pull motion is used, the force required must not be more than 30
pounds.

4.43 Sea Performance-Type II Devices. The device shall meet the
seaworthiness requirements in paragraph 5.2.4 of this appendix and
shall be capable with its equipment of withstanding a saltwater
marine environment for a period of at least 15 days.

5. Tests.

5.1 Material Tests. Testing the material properties specified in
paragraph 3, Materials, of this appendix must be conducted in
accordance with the following test methods or other approved
equivalent methods:

<table bgcolor="#d9d9d9" cellpadding="7" cellspacing="0">
<col/>
<col/>
<col/>
<thead>
<tr>
<td bgcolor="#808080" colspan="3" valign="top">
Test
					Method
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Tests
					Required
</td>
<td bgcolor="#808080">
Federal
					Test Method Standard
</td>
<td bgcolor="#808080">
Other
					Test Method
</td>
</tr>
</thead>
<tbody>
<tr valign="top">
<td bgcolor="#d9d9d9">
Accelerated
					Age
</td>
<td bgcolor="#d9d9d9">
(1.)
					- Method 5850
</td>
<td bgcolor="#d9d9d9">
Per
					Note (2.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Tensile
					Strength (Grab Test)
</td>
<td bgcolor="#d9d9d9">
(1.)
					- Method 5100
</td>
<td bgcolor="#d9d9d9">
Per
					Note (8.) 

</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Tear
					Strength (Trapezoid Test)
</td>
<td bgcolor="#d9d9d9">
(6)
					Method 5136
</td>
<td bgcolor="#d9d9d9">
 

</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Tear
					Strength (Tongue Test)
</td>
<td bgcolor="#d9d9d9">
(1.)
					Method 5134
(Alternate
					to Trapezoid Test paragraph 3.1.5.1)
</td>
<td bgcolor="#d9d9d9">
 

</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Ply
					Adhesion
</td>
<td bgcolor="#d9d9d9">
(1.)
					- Method 5960
</td>
<td bgcolor="#d9d9d9">
Per
					Note (4.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Coat
					Adhesion
</td>
<td bgcolor="#d9d9d9">
(1.)
					- Method 5970
</td>
<td bgcolor="#d9d9d9">
Per
					Note (9.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Permeability
</td>
<td bgcolor="#d9d9d9">
(6.)
					- Method 5460
</td>
<td bgcolor="#d9d9d9">
Per
					Note (7.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Seam
					Shear Strength
</td>
<td bgcolor="#d9d9d9">
(1.)
</td>
<td bgcolor="#d9d9d9">
Per
					Notes (3.) (8.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Seam
					Peel Strength
</td>
<td bgcolor="#d9d9d9">
(1.)
					- Method 5960
</td>
<td bgcolor="#d9d9d9">
Per
					Note (4.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Puncture
					Strength
</td>
<td bgcolor="#d9d9d9">

</td>
<td bgcolor="#d9d9d9">
Per
					Note(10.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Hydrolysis
					Conditioning
</td>
<td bgcolor="#d9d9d9">

</td>
<td bgcolor="#d9d9d9">
Per
					Note (11.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Porosity
					Test (Hydrolysis)
</td>
<td bgcolor="#d9d9d9">
 

</td>
<td bgcolor="#d9d9d9">
Per
					Note (12.)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Flammability
					(Vertical Burn Rate)
</td>
<td bgcolor="#d9d9d9">

</td>
<td bgcolor="#d9d9d9">
Per
					Note (5.)
</td>
</tr>
</tbody>
</table>

NOTES:

(1) Federal Test Method Standard (FTMS) No. 191A dated July 20, 1978.

(2) Samples for the accelerated aging tests must be exposed to a
temperature of 158 ± 5 degrees F for not less than 168 hours. After
exposure, the samples must be allowed to cool to 70 ± 2 degrees F
for neither less than 16 hours nor more than 96 hours before
determining their physical properties in accordance with paragraph
3.1 of this appendix.

(3) Each sample shall consist of two strips 2 inches maximum width by
5 inches maximum length bonded together with an overlap of 3/4 inches
maximum. The free ends must be placed in the testing machine
described in FTMS 191A, Method 5100 and separated at a rate of 12 ±
0.5 inches/minute. The average value of a minimum of three samples
must be reported. Samples may be multilayered to ensure against
premature material failure. Samples may be gripped across the full
two inches of width.

(4) Separation rate must be 2.0 to 2.5 inches/minute. Sample width
shall be one inch.

(5) The material must meet the flammability requirements of 14 CFR §
25.853(a), Appendix F, part I (a)(1)(ii) in effect March 6, 1995.

(6) FTMS No. 191 in effect December 31, 1968.

(7) ASTM Method D1434-82, Procedure V, approved July 30, 1982, is an
acceptable alternate method.

(8) Use of pneumatic grips for holding test samples is an acceptable
alternate to the mechanical grips described in Method 5100.

(9) The sample shall be prepared using the adhesive and construction
methods used to manufacture the evacuation device. Separation rate
must be 2.0 to 2.5 inches/minute.

(10) The fabric shall be tested in a specimen holder constructed in
accordance with figure 1. The fabric shall be clamped tightly in the
specimen holder to present a wrinkle-free surface and prevent
slippage during the test. A piercing instrument with its end
conforming to figure 1 shall be forced against the fabric at
approximately the center of the area enclosed by the specimen holder.
The force required to puncture the specimen shall not be less than
the specified 67 pounds. The test shall be run using a crosshead
speed of 12 inches/minute.

(11) Each sample shall be exposed to a temperature of 136 ± 4
degrees F and a relative humidity of 95 ± 4 percent for a period of
50 days.

(12) Porosity testing conducted for hydrolysis resistance shall be
conducted with the test apparatus specified in paragraph 5.3 or an
equivalent test method approved by the manager of the FAA having
purview of the manufacturer's facilities, as required in paragraphs
3b, Deviations and 5a, Application Data, of this TSO. Note specimen
size and mounting information of paragraphs 5.3.3.1 and 5.3.4.5 of
this appendix. Tests should be conducted at the devices nominal
operating pressure for a duration of 30 minutes. Porosity is
indicated by a loss in chamber pressure during testing. Pressure loss
for material specimens after hydrolysis conditioning shall not be
greater than the pressure loss for the material before conditioning.

![](/static/files/file_jytjXw2lpRK/image012.png)

***FIGURE
1. PIERCING INSTRUMENT AND SPECIMEN HOLDER***

5.2 Functional Tests.

5.2.1 Pressure Retention. Under static conditions and when inflated
and stabilized at the nominal operating pressure, the pressure in
each inflatable chamber of a Type II device must not fall below the
minimum raft mode operating pressure in less than 24 hours. For Type
I, III & IV devices, the pressure in each inflatable chamber must
not fall below 50 percent of the nominal operating pressure in less
than 12 hours.

5.2.2 Overpressure Tests.

5.2.2.1 The device must withstand a pressure at least 1.5 times the
maximum operating pressure for at least 5 minutes without sustaining
damage.

5.2.2.2 At least one specimen of the inflatable device model must be
shown by test to withstand a pressure at least 2 times the maximum
operating pressure without failure for at least 1 minute. Devices so
tested must be clearly identified.

5.2.3 Water Tests-Type II Devices. In either a controlled pool or
fresh water the capacity and buoyancy of the device must be
demonstrated as follows:

5.2.3.1 Both rated and overload capacities established in accordance
with the requirements of paragraph 4.26 of this appendix must be
demonstrated with inflation tubes at minimum raft mode operating
pressure and with the critical buoyancy chamber deflated. The
resultant freeboard in each case must meet the requirements of
paragraph 4.27.2 of this appendix.

5.2.3.2 Persons used in the demonstration must have an average weight
of not less that 170 pounds. Ballast in the form of sand bags or
equivalent may be used to achieve proper loading provided the
appropriate weight distribution within the device is maintained.

5.2.3.3 Persons used in the demonstration must wear FAA approved life
preservers with at least one chamber inflated.

5.2.3.4 The raft equipment required by this TSO, plus one emergency
locator transmitter or a weight simulating a transmitter, must be
aboard the device.

5.2.3.5 Unless it can be shown that there is no tendency for the
device to become inverted during loading and release from the
airplane, it must be demonstrated that the device is self-righting or
that it can be righted by one person in the water, or that while
inverted it can be boarded and provide flotation for the normal rated
capacity.

5.2.3.6 It must be demonstrated that the boarding aids are adequate
for the purpose intended and that it is possible for male and female
adults wearing inflated life preservers to board the raft unassisted.

5.2.4 Sea Trials – Type II Devices. The device must be demonstrated
by tests or analysis, or a combination of both, to be seaworthy in an
open sea condition with maximum sustained winds of 17 to 27 knots and
waves of 6 to 10 feet. In tests, ballast in the form of sand bags or
equivalent may be used to achieve proper loading provided the
appropriate weight distribution within the raft is maintained. If
analysis is used, the analysis must be approved by the manager of the
FAA office having purview of the manufacturer's facilities as
required in paragraph 5a, Application Data of this TSO. For this
seaworthiness demonstration, the following apply -

5.2.4.1 The raft must be boarded by the rated number of occupants to
demonstrate the method of loading from a simulated aircraft sill
installation.

5.2.4.2 The proper functioning of the means to separate the raft from
the simulated aircraft installation must be demonstrated.

5.2.4.3 All equipment required by this TSO must be aboard and the
proper functioning of each item of equipment must be demonstrated.

5.2.4.4 The canopy must be erected for a sufficient time to assess
its resistance to tearing and the protection it affords. The method
of erection must be shown to be accomplished by one occupant of an
otherwise empty raft and by occupants of a raft filled to rated
capacity.

5.2.4.5 The stability of the raft must be demonstrated when occupied
at normal rated capacity and at 50 percent rated capacity.

5.3 Radiant Heat Test. The pressure holding materials in the
emergency evacuation inflatable device shall be tested for resistance
to radiant heat in accordance with this standard. If any of the outer
surface of the pressure holding material is altered by marking, by
lettering, by affixed overlay or underlying material, or in any other
manner which affects radiant heat resistance, the altered material
shall also be tested.

5.3.1 Criteria for Acceptance. For each material which requires
testing, at least three specimens shall be tested at 1.5 Btu/ft2-sec
(1.7 W/cm2), and the resulting times to failure averaged.
The average time to failure may not be less than 180 seconds with no
value less than 90 seconds. Time to failure is the time between first
application of heat to the specimen and first drop in pressure below
the maximum pressure attained in the test cylinder during the test.

5.3.2 Test Apparatus. The tests shall be conducted using the FAA
Slide Material Radiant Heat Apparatus, or another equivalent test
apparatus and test method approved by the manager of the FAA office
having purview of the manufacturer's facilities as required in
paragraphs 3b, Deviations, and 5a, Application Data of this TSO. The
apparatus consists of a horizontally mounted cylinder closed at one
end and fitted with a source of air pressure and pressure
measurement. A specimen holder clamped over the open end seals the
cylinder air tight with the material specimen acting as a pressure
holding diaphragm. The cylinder and specimen holder are mounted on a
pivot and slide bar, and can be positioned at varying distances from
a 3-inch (76mm) diameter electric radiant heat furnace and a
calorimeter. The test apparatus is described in figures 2 through 5
and paragraphs 5.3.2.1 through 5.3.2.6 of this appendix.

5.3.2.1 The pressure cylinder and specimen holder, as shown in
figures 2, 3, and 4 of this appendix, consist of a 7-inch (178 mm)
outside diameter (O.D.) by 6 1/2-inch (165 mm) inside diameter (I.D.)
by 12 3/8-inch (314 mm) long aluminum tube. On one end of the tube is
welded a 1/2-inch (13 mm) thick aluminum plate, drilled and tapped
for a 1/4-inch American national pipe taper thread to facilitate air
pressure and pressure recording hookups. On the other end of the tube
is welded a 7-inch (178 mm) O.D. by 5 1/2-inch (140 mm) I.D. ring of
1/2-inch (13 mm) thick aluminum. This ring is drilled and tapped for
10-32 by 7/8-inch (22 mm) long studs. Another 6 3/4-inch (171 mm)
O.D. by 5 1/2-inch (140 mm) I.D. by 1/2-inch (13 mm) thick aluminum
ring and two neoprene rubber gaskets with matching clearance holes to
fit over the studs provide a means for clamping and sealing the test
specimen in place. Hinges and adjustable stops are welded to the
sides of the cylinder, shown in figures 2, 3, and 4.

5.3.2.2 The electric furnace meeting the requirements of the FAA Fire
Test Handbook is shown in figure 5 of this appendix. It has a 3-inch
(76 mm) diameter opening to provide a constant irradiance on the
specimen surface. An acceptable furnace, part number 680860025700, is
available from Newport Scientific, Inc., 8246-E Sandy Court, Jessup,
Maryland 20794-9632. Another acceptable furnace, part number
680860380000, is also available from Newport Scientific, Inc.

5.3.2.3 A 0-5 Btu/ft2-sec (5 W/cm2) calorimeter meeting
the requirements of the FAA Fire Test Handbook is required. (Vatell
thermogage calorimeter no. 1000-1B, available from Vatell, P.O. Box
66, Christiansbury, Virginia 24073, is acceptable.) The calorimeter
is mounted in a 4 1/2-inch diameter by 3/4-inch insulating block and
is hinged to one of the sliding bars of the framework. The surface of
the calorimeter is flush with the surface of the insulating block and
centered with the furnace. See figure 4 of this appendix. The
calorimeter must be calibrated to a primary standard by NIST or
calibrated per the requirements of [appendix
4](#_DxCrossRefBm920220754).

5.3.2.4 The pressure cylinder, calorimeter, and furnace are mounted
on a framework as detailed in figure 4 of this appendix. Adjustable
sliding stops are located on each of the bars for setting the
cylinder and calorimeter at the desired distance from the opening of
the furnace.

5.3.2.5 Compressed air is connected to the cylinder through a needle
valve attached to the end of the framework. A tee on the outlet side
of the valve provides for a 0-5 psig pressure gauge, transducer, and
flexible tube to supply air to the rear plate of the pressure
cylinder, as shown in figure 2 of this appendix.

5.3.2.6 The outputs of the calorimeter and pressure transducer are
measured and recorded using a recording potentiometer or other
suitable instrument capable of measurement over the range required.

![Picture 8](/static/files/file_jytjXw2lpRK/image013.png)

![](/static/files/file_jytjXw2lpRK/image014.png)

![csETSOimage7.png](/static/files/file_jytjXw2lpRK/image015.png)

![](/static/files/file_jytjXw2lpRK/image016.png)

5.3.3 Test Specimens.

5.3.3.1 Test specimens 7 inches (178mm) in diameter with 1/4-inch
(6mm) holes punched in the material to match the studs in the
pressure cylinder must be cut from the material to be tested.

5.3.3.2 Test specimens must be conditioned at 70 ± 3 degrees F (21±3
degrees C) and 50 ±5 percent relative humidity for at least 24 hours
prior to testing.

5.3.4 Test Procedures.

5.3.4.1 All tests must be conducted in a draft free room or enclosed
space.

5.3.4.2 After turning on the radiant heat furnace and other required
instrumentation, allow 1/2 to 3/4 hour to stabilize heat output and
for instrumentation warm-up.

5.3.4.3 Adjust transformer to produce a radiant heat flux of 2
Btu/ft2-sec (2.3 W/cm2) when the calorimeter is
positioned 1 1/2 inches (38mm) in front of the radiant heat furnace.

5.3.4.4 Find the location in front of the furnace for the test heat
flux of 1.5 Btu/ft2-sec (1.7 W/cm2) by sliding the
calorimeter on the horizontal bar and fixing the position with the
sliding stop. Swing the calorimeter out of position.

5.3.4.5 Mount the specimen on the open end of the cylinder with a
neoprene gasket on each side of the specimen with the reflective
surface of the material facing the furnace. Place the aluminum ring
on the studs and tighten the nuts so that an airtight seal made.

5.3.4.6 Pressurize the cylinder to the device nominal operating
pressure. Check for leakage.

5.3.4.7 Check the distance from the radiant heat furnace to the
surface of the test specimen. This distance is the same as the
distance to the surface of the calorimeter.

5.3.4.8 Place the calorimeter in front of the radiant heat furnace
and record the heat flux. An acceptable heat flux is 1.5 Btu/ft2-sec
(1.7 W/cm2). Remove calorimeter.

5.3.4.9 Place the pressure cylinder and test specimen in front of the
radiant heat furnace. Start timer or note starting time on the
recorder.

5.3.4.10 Pressure is monitored from the time the specimen is placed
in front of the furnace until initial pressure loss is observed.

5.4 Evacuation Rate Tests.

5.4.1 Basic Test Conditions. The following test conditions shall be
applicable to tests run for showing compliance with paragraph 4.10.1
of this appendix:

5.4.1.1 The device shall be tested at normal sill height.

5.4.1.2 The device shall be tested at three different inflation
pressures: minimum operating, maximum operating, and the nominal
operating pressure.

5.4.1.3 The surface of the device shall be dry.

5.4.1.4 The test area may be illuminated to any level suitable for
safe conduct of the test.

5.4.1.5 The evacuees may be of any age, gender, weight, or experience
level suitable for safe conduct of the test, but each evacuee group
must average a minimum of 170 pounds per person. Evacuees may
participate in more than one test run.

5.4.1.6 Each device lane shall be traversed by a minimum of 20
evacuees per lane for each test run.

5.4.1.7 All test runs shall be on the same test article.

5.4.1.8 Each test run must have a rate of 60 evacuees/minute per lane
or higher.

5.4.1.9 The combined average rate of all test runs must be 70
evacuees/minute per lane or higher. If different numbers of evacuees
are used among the different test runs, the rates for each test run
shall be mathematically weighted to ensure proper averaging.

5.4.2 Maximum and Minimum Sill Height Conditions. In addition to the
tests in paragraph 5.4.1 above, the device shall be tested at the
maximum and minimum sill heights. Three test runs shall be conducted
on the same test article for both sill heights, one each at minimum
operating, maximum operating, and the nominal operating pressure of
the normal conditions pressure range. At maximum sill height, a
minimum of five evacuees per lane per run shall use the device and be
conveyed safely to the ground. At minimum sill height, a minimum of
20 evacuees per lane per run shall use the device. The evacuees shall
meet the same requirements as in paragraph 5.4.1.5 of this appendix.
No specific evacuation rate is required for the maximum sill height
tests. However, at minimum sill height the rate shall be no less than
that shown in paragraph 5.4.3.10.

5.4.3 Emergency Lighting Test Conditions. The following test
conditions shall be applicable to tests run for showing compliance
with paragraph 4.10.2 of this appendix:

5.4.3.1 The test shall be run on the airplane on which installation
is intended or an approved, representative mock-up of the relevant
section of the airplane.

5.4.3.2 The sill height used shall represent normal conditions for
the airplane with all landing gear extended.

5.4.3.3 When using a mock-up, the exit cutout and the door (if
necessary) shall be representative of the airplane. The passageway to
the exit should be no greater than the minimum specified for that
exit in 14 CFR § 25.813, e.g., 36 inches wide for a Type A or B
exit, or 20 inches wide for a Type I, II or C exit. The assist space
shall be per current FAA guidance contained in AC 25-17. Cabin
features such as doors, cabinets, monuments, door hinges, or other
impediments intruding into the exit path which may influence the
evacuation rate shall be realistically simulated along the length of
the passageway.

5.4.3.4 The device shall be installed, inflated to its nominal
operating pressure and ready for use. Note: Emergency lights mounted
on the device shall not be illuminated until test initiation, and
shall be powered by batteries conditioned per 14 CFR § 25.812(i), or
an equivalent power supply.

5.4.3.5 The surface of the device shall be dry.

5.4.3.6 The device shall be hidden from view of the evacuees prior to
test initiation.

5.4.3.7 For a period of 5 minutes prior to the initiation of the
test, the area holding the evacuees, i.e., the "cabin interior",
shall be illuminated to a minimum level of 5 foot-candles, or the
level which is representative of typical cabin lighting as measured
on the centerline of the passageway floor, one foot inboard of the
exit sill. The ambient illumination in the test area outside of the
airplane or mock-up shall not exceed 0.005 foot-candles; measurements
should be made at the ground end of the assisting means and at the
exit, just outside of the fuselage. Provisions shall be made, where
necessary, to prevent light reflecting off of surfaces in the outside
test area, e.g., hangar walls, from providing visual references to
the test participants. All illumination measurements shall be made
with a light meter in current calibration, with an
accuracy/resolution of at least 2 percent and 0.001 foot-candles.

5.4.3.8 Upon test initiation, the illumination of the "cabin
interior" shall be reduced to the nominal light level provided
by the airplane emergency lighting system (with batteries conditioned
per 14 CFR § 25.812(i)) as measured as incident light on the
centerline of the passageway floor, one foot inboard of the exit
sill. The assist means lighting system(s) will be activated.

5.4.3.9 The evacuees shall not have participated in any test or
demonstration involving airplane evacuation devices within the past
year.

5.4.3.10 The evacuee group size shall be per the following table:

<table bgcolor="#d9d9d9" cellpadding="7" cellspacing="0">
<col/>
<col/>
<col/>
<col/>
<tr>
<td bgcolor="#808080">
Exit
				type
</td>
<td bgcolor="#808080">
Rating
</td>
<td bgcolor="#808080">
Evacuees
</td>
<td bgcolor="#808080">
Pass/fail
				criterion (in seconds)***
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
A
</td>
<td bgcolor="#d9d9d9">
110
</td>
<td bgcolor="#d9d9d9">
44
				(22 per lane)
</td>
<td bgcolor="#d9d9d9">
30
				+Tt****
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
B
</td>
<td bgcolor="#d9d9d9">
75
</td>
<td bgcolor="#d9d9d9">
45
				(22/23 per lane)
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
C
</td>
<td bgcolor="#d9d9d9">
55
</td>
<td bgcolor="#d9d9d9">
22
</td>
<td bgcolor="#d9d9d9">
30
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
I
</td>
<td bgcolor="#d9d9d9">
45
</td>
<td bgcolor="#d9d9d9">
27
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
II
</td>
<td bgcolor="#d9d9d9">
40
</td>
<td bgcolor="#d9d9d9">
24
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
III
</td>
<td bgcolor="#d9d9d9">
35
</td>
<td bgcolor="#d9d9d9">
21
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
III
				(dual*)
</td>
<td bgcolor="#d9d9d9">
70
</td>
<td bgcolor="#d9d9d9">
42
				(21 per III)
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
III
				(dual**)
</td>
<td bgcolor="#d9d9d9">
70
</td>
<td bgcolor="#d9d9d9">
39
				(19/20 per III)
</td>
<td bgcolor="#d9d9d9">
45
				+Tt
</td>
</tr>
</table>

\* Dual separated by >= 3 seat rows.

\*\* Dual separated by < 3 seat rows.

\*\*\* The total time allowed from the start of the test, when the light
level changes, as described in 5.4.3.8, until the last evacuee
reaches the ground.

\*\*\*\* Tt = Transit time (Tt), determined by averaging the times
required by five or more evacuees tested one at a time to traverse
the descent route in factory ambient lighting conditions. Evacuees
must meet the conditions in 5.4.3.9 and 5.4.3.11.

5.4.3.11 The age/gender mix of the evacuee group shall be as defined
in the current version of Appendix J of 14 CFR part 25.

5.4.3.12 For floor level exits, a person trained to give verbal
commands shall direct the evacuation from an assist space provided
for the aircraft and may stop the test if conditions warrant. He/she
should use procedures or techniques approved by the manager of the
ACO having purview of the device manufacturer’s facilities. These
procedures and techniques shall not include physically assisting
hesitant evacuees through the doorway.

5.4.3.13 The following information may be given to participants and
the following procedures may occur during the briefings identified
below:

5.4.3.13.1 Recruiting briefing:

— Describe purpose of the test.

— Identify possible hazards of the
test.

— Identify benefits for test
participants.

— Identify benefits to airline
passengers.

— Describe types of
clothing/footwear required.

5.4.3.13.2 Orientation briefing:

— Get subject characteristics.

— Check for appropriate clothing
and footwear.

— Prepare paperwork (medical
forms, etc.).

— Give building safety information
(fire evacuation plan, etc.).

— Describe test and procedures.

— Show pictures of the device from
ground level in daylight.

— Describe how to enter the device
using pictures from ground level, if desired.

— Get informed consent.

5.4.3.13.3 Final briefing:

— Escort to test area.

— Escort into test mock-up (also
known as test module) to prepare for test.

— Describe test procedures again.

— Line up (position) evacuees at
the exit(s) in single or dual lanes, as appropriate, for the test.

— Begin test protocol.

5.5 Beam Strength Tests-Except Type III Devices.

5.5.1 Basic Test Conditions. The following test conditions shall be
applicable to tests run to show compliance with paragraph 4.3.1 of
this appendix.

5.5.1.1 Sand Bags.

5.5.1.1.1 Three sand bags, each weighing a minimum of 170 pounds,
connected in series, are required for each and every lane of the
device.

5.5.1.1.2 All sand bags shall be equal to each other in weight within
5.0 lbs.

5.5.1.1.3 A single 170-pound sand bag may be assembled from two or
more smaller bags for ease of handling. The smaller bags need not be
of equal weight.

5.5.1.1.4 The outer covering of the sand bag shall be a material
having a coefficient of friction of at least 0.4 when tested per ASTM
Standard D 1894-95. (This value is typical of some cotton and
polyester/cotton material blends. Test data for the material used
shall be included with the final test report.)

5.5.1.1.5 Filler materials other than sand may be used, however,
liquids are not acceptable unless they are sufficiently constrained
to prevent shifting within the bag.

5.5.1.1.6 The basic shape of a sand bag should be a rectangular solid
with rounded corners and a minimum contact surface width of 15
inches. The bag should be longer than it is wide and the height
should be less than the width.

5.5.1.1.7 Provisions to securely connect the three sand bags to each
other shall be included on each bag. The interconnection provisions
shall be designed to minimize any tendency for the bags to roll or
tumble.

5.5.1.1.8 When connected, the three sand bags shall occupy an area
not to exceed 7.5 feet by 2 feet.

5.5.1.2 Delivery System.

5.5.1.2.1 A delivery system shall be used to convey the sand bags to
the beginning of the down-slide portion of the device and to release
them so that they may slide down the device. The vertical offset of
the end of the delivery system and the device at the point of
delivery should be minimized to minimize tumbling of the sandbags.

5.5.1.2.2 The delivery system shall consist of a flat, rigid plane a
maximum of 8 feet in length covered with material similar to that
used on the sliding surface of the device.

5.5.1.2.3 The delivery system shall incorporate provisions for slowly
elevating the rear portion of the plane until the sand bags will
begin to move downward onto the sliding surface solely by the effect
of gravity or until the plane is at the same angle as the sliding
surface and acts as a seamless extension to it. Angles between these
two points are acceptable, but in no case shall the angle of the
plane exceed the angle of the sliding surface. The sand bags should
be restrained until test initiation.

5.5.1.2.4 Where a straight delivery system design cannot be used
because the device has a ramp or porch or is more than 20 degrees
from being perpendicular to the fuselage, an alternate delivery
system design may be used if approved in advance by the manager of
the ACO having purview of the manufacturer’s facilities.

5.5.1.3 Device Configuration and Installation.

5.5.1.3.1 The device shall be in its production-deliverable
configuration with all required equipment installed.

5.5.1.3.2 The sliding surface of the device shall be dry and new
(i.e. never having been subjected to persons or sand bags sliding on
its surface prior to the tests).

5.5.1.3.3 The pressure in each and every chamber of the device shall
be its nominal operating pressure.

5.5.1.3.4 The device shall be installed at its normal sill height and
with its normal attachment means. If the device is intended for use
at more than one exit pair, it shall be tested at the normal sill
height for each exit pair.

5.5.1.3.5 The width of the exit through which the sand bags are
delivered shall be representative of the airplane exit to which the
device will normally be attached and where the evacuees would
normally enter the device. For devices not mounted at the exit sill,
only the airplane structure which would control evacuee flow onto the
device needs to be simulated.

5.5.2 Testing.

5.5.2.1 For a multi-lane device, the sand bags for all lanes shall be
launched simultaneously or as nearly so as possible. A single
mechanism which will provide simultaneous release of all bags is
recommended. In no case shall the sand bags be launched with an
offset of more than one sand bag length difference among all the
lanes. A case not conforming to this requirement shall be considered
a non-test.

5.5.2.2 Sand bags shall not overlap or lie atop one another at test
initiation.

5.5.2.3 Sand bags shall not roll or tumble more than 180 degrees
either by force of launch or through action of movement down the
device. Some tumbling of the sand bags at the bottom of the device
due to the effects of the deceleration means is acceptable.

5.5.2.4 Sand bags shall not depart the device except at the bottom
end where evacuee contact with the ground is intended.

5.5.2.5 Cross-over of the sand bags from one lane to another on a
multiple lane device is acceptable.

5.5.3 Success Criteria.

5.5.3.1 For the test article to be deemed acceptable, the test shall
be completed successfully three consecutive times. (Tests which are
aborted or considered non-tests, e.g., there is more than one sand
bag offset between lanes during the start of a multiple lane device
test, do not count against the goal of three consecutive successful
tests.)

5.5.3.2 All sand bags in all lanes shall completely depart the end of
the device, or shall be deemed to be likely to exit the device if not
obstructed by bags which are partially on the ground and partially on
the device.

5.5.3.3 The bottom of the sliding surface shall not contact the
ground at any time.

5.5.3.4 The device, without repair, shall meet the requirements of
paragraph 4.10.1 of this appendix after being subjected to this test.

5.5.4 Alternative Test Method. As an alternative to the test method
(using sand bags) described in paragraph 5.5.1, a test using human
subjects may be conducted as follows:

5.5.4.1 Test Subjects. Prior to testing, all test subjects shall be
briefed on safety and test issues per paragraph 5.4.3.13 of this TSO.
The briefing shall include instructions for required behavior while
participating in the test. While test subjects may be experienced,
they shall not behave in a prohibited manner. Prohibited behavior
includes shifting of body weight and/or use of hands and/or feet to
“propel oneself’ along the slide surface in order to depart the
end of the device.

5.5.4.2 Device Configuration and Installation.

5.5.4.2.1 The device shall be in its production-deliverable
configuration with all required equipment installed.

5.5.4.2.2 The sliding surface of the device shall be dry and new
(i.e. never having been subjected to persons or sand bags sliding on
its surface prior to the tests).

5.5.4.2.3 The pressure in each and every chamber of the device shall
be its nominal operating pressure.

5.5.4.2.4 The device shall be installed at its normal sill height and
with its normal attachment means. If the device is intended for use
at more than one exit pair, it shall be tested at the normal sill
height for each exit pair.

5.5.4.2.5 The width of the exit through which the test subjects would
pass before entering the device shall be representative of the
airplane exit where the device will normally be attached and where
the evacuees would normally enter the device. For devices not mounted
at the exit sill, only the airplane structure which would control
evacuee flow onto the device needs to be simulated.

5.5.4.3 Test Protocol. The following test protocol, which is
applicable for single or multiple lane devices, shall be used:

5.5.4.3.1 The test subjects’ clothing which contacts the device
surface shall be made of material with a coefficient of friction of
at least 0.4 per ASTM Standard D1894-90 (typical of cotton or
polyester/cotton blend).

5.5.4.3.2 Each test subject shall weigh at least 170 pounds.

5.5.4.3.3 For each lane of the device, three test subjects shall be
seated “toboggan” style. The legs of the second and third person
in each group shall straddle the person ahead. The first and second
persons in the group shall grasp the legs of the person behind them.

5.5.4.3.4 The first person in the group should be located entirely on
the downward portion of the device, i.e., he/she would slide if not
holding onto the legs of the person behind. The second person in the
group should be located either entirely on the downward portion of
the device or at the transition point between the door sill or device
ramp and the downward portion of the device. The third person should
be on the door sill or device ramp, i.e., would not slide if not
holding onto anything or being held by the legs by the second person
in the group.

5.5.4.3.5 For each group, the distance from the front of the first
test subject’s torso to the back of the third test subject’s
torso shall not exceed 7.5 feet at the initiation of sliding by the
third (last) person in the group.

5.5.4.3.6 At the test conductor’s word “go”, the test subjects
in each lane will proceed down the slide together. For multiple lane
devices, simultaneous push-off is required for all lanes, i.e., no
more than a one-person offset is permissible among all lanes. Minor
pushing off, particularly by the second and third persons in each
group, is allowed to start the group sliding. Additional persons are
allowed to gently push the last person in each group to start the
sliding process.

5.5.4.3.7 After the third person in each group has started to slide,
that person may signal the two others in the group to let go of the
legs by yelling “OK” or “Let go.”

5.5.4.3.8 Upon hearing that signal, the first two persons in the
group should let go of the others’ legs in order to provide freedom
of movement for exiting the device and moving out of the way. After
releasing the legs, the test subjects shall not engage in pushing,
scooting or shifting of weight in order to exit the device. As soon
as foot contact with the ground is made, the test subjects may stand
immediately and move away quickly.

5.5.4.3.9 The first and second persons in the group are to stand and
move away quickly when exiting the device to prevent blocking the
person behind them.

5.5.4.3.10 As an alternative to paragraph 5.5.4.3.4, a delivery
system can be used to convey the test subjects to the beginning of
the down-slide portion of the device. See paragraph 5.5.1.2.2 through
5.5.1.2.4 for description of the delivery system.

5.5.4.4 Success Criteria.

5.5.4.4.1 For the device to be deemed acceptable, the test must be
completed successfully three consecutive times. (Tests which are
aborted or considered non-tests, e.g., there is more than a one
person offset between lanes during the start of a multiple lane
device, do not count against the goal of three consecutive successful
tests.)

5.5.4.4.2 The first two test subjects in each and every lane shall
exit the end of the device with continuous motion. The third person
should also exit the device with continuous motion, but may stay on
the device if his/her motion was stopped by the person in front of
him/her. Crossover of persons from one lane to another on a multiple
lane device is acceptable; however, no more than one person may
remain on the device in any lane.

5.5.4.4.3 The underside of the sliding surface shall not contact the
ground at any time.

5.5.4.4.4 None of the test subjects shall perform prohibited
movements (as described above).

5.5.4.4.5 The device, without repair, shall meet the requirements of
paragraph 4.10.1 of this appendix after being subjected to this test.

5.6 Attachment Means Tests - Girt (See figure 6 of this appendix.).

5.6.1 Symmetric Girt Tensile Load Test. A representative production
configuration girt including attachments to the device and the
aircraft shall be installed to produce a symmetric load in a tensile
test machine. The girt shall be attached on one end using the girt
bar, or equivalent, and on the other end to the normal girt
attachment means to the inflatable device. The slide fabric to which
the girt attachment is bonded shall be fastened to a steel plate or
around a cylinder designed to represent the inflatable to which the
girt is attached (See figure 6 of this appendix). The girt shall be
able to withstand a test load which is equal to the maximum expected
in-use load multiplied by a factor of 1.5 (as required by paragraph
4.8 of this appendix). The in-use load is a combination of all the
loads acting on the girt attachments during any individual test run.
The loads shall be established by instrumenting the girt
attachment(s) to a test module simulating the aircraft fuselage and
measuring the forces transmitted to the attachment(s) during
deployment and use of the device. (The means for measuring the peak
loads must be shown to be reliable, accurate, in calibration, and
appropriate for the type of testing. If the means is a data
acquisition system utilizing an analog-to-digital converter, see
appendix 3 of this TSO for guidance.) The use conditions shall
include, but not be limited to, those encountered in demonstrating
compliance with the requirements of paragraphs 4.3.1, 4.10, 4.11,
4.12, 4.13, 4.20, 4.21, 4.22, 4.23, 4.28, 5.2.4 and 5.8 of this
appendix. The test load shall be applied to the girt for 60 seconds.
During the test, tearing of the girt is not acceptable. Deformation
of the girt is acceptable if it would not prevent continued safe use
of the device in an actual evacuation.

5.6.2 Asymmetric Girt Tensile Load Test. A representative production
configuration girt shall be installed to produce an asymmetric load
in a tensile test machine and an asymmetric load shall be applied.
The girt shall be attached on one end using the girt bar, or
equivalent, and on the other end to the normal girt attachment means
to the inflatable device. The slide fabric to which the girt
attachment is bonded shall be fastened to a steel plate designed to
represent the inflatable to which the girt is attached (See figure 6
of this appendix). The girt shall be able to withstand a test load
applied asymmetrically by pulling the steel plate away from the
secured girt bar at a point even with the edge of the girt. The test
shall be repeated for each side of the device girt. The test load(s)
is equal to the maximum expected in-use load multiplied by a factor
of 1.5 (as required by paragraph 4.8 of this appendix). The in-use
load shall be established by instrumenting each girt attachment to
the aircraft and measuring the forces transmitted to the attachment
during deployment and use of the device. (The means for measuring the
peak loads must be shown to be reliable, accurate, in calibration,
and appropriate for the type of testing. If the means utilizes an
analog to digital converter, see [appendix
3](#_DxCrossRefBm920220753) of this TSO for guidance.) The use conditions shall
include, but not be limited to, those encountered in demonstrating
compliance with the requirements of paragraphs 4.20, 4.21, 4.28,
5.2.4 and 5.8 of this appendix. The test load shall be applied to the
edge of the girt for 60 seconds. During the test, tearing of the girt
is not acceptable. Deformation of the girt is acceptable if it would
not prevent continued safe use of the device in an actual evacuation.

![](/static/files/file_jytjXw2lpRK/image017.png)

\* DRUM SHALL RETAIN ITS SHAPE
THROUGHOUT TEST LOADING AND SHALL BE OF SUFFICIENT DIAMETER TO ALLOW
SIMULATION OF THE GIRT ATTACHMENT ANGLE, A.

***Figure
6. Typical Girt Loading Test Set-Up***

5.7 Attachment Means Tests - Other Than a Girt. When the attachment
means is other than a girt, e.g., a number of narrow straps attached
at different locations on the aircraft, only the straight tensile
test is necessary for each of the straps. A representative production
configuration of each of the straps, including its attachment to the
device and to the airplane, shall be individually installed to
produce a symmetric load in a tensile test machine. Each strap shall
be able to withstand a test load which is equal to the maximum
expected in-use load multiplied by a factor of 1.5 (as required by
paragraph 4.8 of this appendix). The in-use load shall be established
by instrumenting each strap attachment to a test module simulating
the aircraft fuselage and measuring the forces transmitted to that
attachment during deployment and use of the device. The use
conditions shall include, but not be limited to, those encountered in
demonstrating compliance with the requirements of paragraphs 4.3.1,
4.10, 4.11, 4.12, 4.13, 4.20, 4.21, 4.22, 4.23, 4.28, 5.2.4 and 5.8
of this appendix. The test load shall be applied to the strap for 60
seconds. During the test, tearing of the strap is not acceptable.
Deformation of the strap is acceptable, if it would not prevent
continued safe use of the device in an actual evacuation.

5.8 Attachment Means - Pontoon Loading Tests. If the device is
equipped with outrigger pontoons (also known as sponsons) which can
be inadvertently entered by evacuees during an emergency evacuation,
the following test shall be conducted on each side:

5.8.1 The device shall be installed at normal sill height and
inflated to the minimum value of the normal conditions pressure
range.

5.8.2 Weights that represent 170 pound individuals shall be placed in
the pontoon(s) at the bottom outside area on one side of the device.
The number of individuals to be simulated shall be based on the
length, in feet, of the occupiable portion of the pontoon divided by
4.5. Any remainder from the division may be discarded.

5.8.3 An evacuee group of twenty persons shall jump into the device
at an average rate of 70 per minute (after the first jumper, the last
19 have 16 seconds to jump into the device). The evacuee group shall
average at least 170 pounds per person. In the case of multi-lane
devices, the evacuees will jump only into the lane adjacent to the
loaded pontoon. The evacuees may be of any age, gender, and
experience level.

5.8.4 To pass this test, the means of attachment to the aircraft
shall not tear or rip, and no evacuee shall enter the pontoon area or
fall off the device.

5.9 Hot & Cold Soak Test Protocol.

5.9.1 Stabilize the normally charged stored gas bottle to a
temperature of 70 ± 5 degrees F, then, for the cold test only,
reduce the stored gas bottle pressure to the minimum dispatch
pressure. As an alternate, the bottle may be charged directly to the
minimum dispatch pressure for the cold test. However, for mixed-gas
systems, the ratio of the gas mix must be maintained.

5.9.2 Thermally condition the device for at least 16 hours according
to the following table:

<table bgcolor="#d9d9d9" cellpadding="7" cellspacing="0">
<col/>
<col/>
<tr valign="top">
<td bgcolor="#808080">
Condition
</td>
<td bgcolor="#808080">
Temperature
				(degrees F)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Hot
				Soak
</td>
<td bgcolor="#d9d9d9">
=
				160 (for all devices)
</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Cold
				Soak
</td>
<td bgcolor="#d9d9d9">
=
				-40 (for devices installed in the pressurized cabin) 

</td>
</tr>
<tr valign="top">
<td bgcolor="#d9d9d9">
Cold
				Soak
</td>
<td bgcolor="#d9d9d9">
=
				-65 (for devices installed outside the pressurized cabin)
</td>
</tr>
</table>

5.9.3 Deploy the device into ambient temperature conditions
(typically defined as between 65 and 85 degrees F) from the
appropriate airplane door or a suitable airplane door mock-up or
module, within 10 minutes after removal from the conditioning
chamber.

5.9.4 To be considered acceptable, the unit should deploy and inflate
into a useable attitude and achieve minimum operating pressure in all
inflation chambers but should not exceed the specified maximum
operating pressure. The pressure reading should be taken as soon as
possible but no later than one minute after deployment.