Special Conditions: ATR Model ATR-42-200/-300/-320/-500 and ATR-72-102/-202/-212/-212A Airplanes; Seats With Non-Traditional, Large, Non-Metallic Panels, 49871-49873 [2016-17846]
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Federal Register / Vol. 81, No. 146 / Friday, July 29, 2016 / Rules and Regulations
a change to the type certificate to
include another model incorporating the
same novel or unusual design feature,
these special conditions would apply to
that model as well.
Conclusion
This action affects only certain novel
or unusual design features on one model
series of airplanes. It is not a rule of
general applicability.
The substance of these special
conditions has been subjected to the
notice and comment period in several
prior instances and has been derived
without substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. Therefore, because a
delay would significantly affect the
certification of the airplane, the FAA
has determined that prior public notice
and comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions upon
publication in the Federal Register. The
FAA is requesting comments to allow
interested persons to submit views that
may not have been submitted in
response to the prior opportunities for
comment described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
asabaliauskas on DSK3SPTVN1PROD with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for Embraer Model
EMB–550 and Model–545 series
airplanes.
In addition to the requirements of
§§ 25.562 and 25.785, and special
conditions no. 25–495–SC, the
following special conditions are part of
the type certification basis for the
Embraer Model EMB–545 and EMB–550
series airplanes with leg-flail airbags
installed on side-facing seats.
1. For seats with a leg-flail airbag
system, the system must deploy and
provide protection under crash
conditions where it is necessary to
prevent serious injury. The means of
protection must take into consideration
a range of stature from a 2-year-old child
to a 95th-percentile male. At some
buttock popliteal length and effective
seat-bottom depth, the lower legs will
not be able to form a 90-degree angle
relative to the upper leg; at this point,
VerDate Sep<11>2014
17:04 Jul 28, 2016
Jkt 238001
the lower leg flail would not occur. The
leg-flail airbag system must provide a
consistent approach to prevention of leg
flail throughout that range of occupants
whose lower legs can form a 90-degree
angle relative to the upper legs when
seated upright in the seat. Items that
need to be considered include, but are
not limited to, the range of occupants’
popliteal height, the range of occupants’
buttock popliteal length, the design of
the seat effective height above the floor,
and the effective depth of the seatbottom cushion.
2. The leg-flail airbag system must
provide adequate protection for each
occupant regardless of the number of
occupants of the seat assembly,
considering that unoccupied seats may
have an active leg-flail airbag system.
3. The leg-flail airbag system must not
be susceptible to inadvertent
deployment as a result of wear and tear,
or inertial loads resulting from in-flight
or ground maneuvers (including gusts
and hard landings), and other operating
and environmental conditions
(vibrations, moisture, etc.) likely to
occur in service.
4. Deployment of the leg-flail airbag
system must not introduce injury
mechanisms to the seated occupant, or
result in injuries that could impede
rapid egress.
5. Inadvertent deployment of the legflail airbag system, during the most
critical part of the flight, must either
meet the requirement of § 25.1309(b), or
not cause a hazard to the airplane or its
occupants.
6. The leg-flail airbag system must not
impede rapid egress of occupants from
the airplane 10 seconds after airbag
deployment.
7. The leg-flail airbag system must be
protected from lightning and highintensity radiated fields (HIRF). The
threats to the airplane specified in
existing regulations regarding lightning
(§ 25.1316) and HIRF (§ 25.1317) are
incorporated by reference for the
purpose of measuring lightning and
HIRF protection.
8. The leg-flail airbag system must
function properly after loss of normal
airplane electrical power, and after a
transverse separation of the fuselage at
the most critical location. A separation
at the location of the leg-flail airbag
system does not have to be considered.
9. The leg-flail airbag system must not
release hazardous quantities of gas or
particulate matter into the cabin.
10. The leg-flail airbag system
installation must be protected from the
effects of fire such that no hazard to
occupants will result.
11. A means must be available to
verify the integrity of the leg-flail airbag
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Fmt 4700
Sfmt 4700
49871
system’s activation system prior to each
flight, or the leg-flail airbag system’s
activation system must reliably operate
between inspection intervals. The FAA
considers that the loss of the leg-flail
airbag system’s deployment function
alone (i.e., independent of the
conditional event that requires the legflail airbag system’s deployment) is a
major-failure condition.
12. The airbag inflatable material may
not have an average burn rate of greater
than 2.5 inches per minute when tested
using the horizontal flammability test
defined in part 25, appendix F, part I,
paragraph (b)(5).
13. The leg-flail airbag system, once
deployed, must not adversely affect the
emergency-lighting system (i.e., block
floor-proximity lights to the extent that
the lights no longer meet their intended
function).
Issued in Renton, Washington, on July 21,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–17845 Filed 7–28–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2016–8246; Special
Conditions No. 25–624–SC]
Special Conditions: ATR Model ATR–
42–200/–300/–320/–500 and ATR–72–
102/–202/–212/–212A Airplanes; Seats
With Non-Traditional, Large, NonMetallic Panels
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
These special conditions are
issued for ATR Model ATR–42–200/–
300/–320/–500 and ATR–72–102/–202/
–212/–212A airplanes. These airplanes
will have a novel or unusual design
feature when compared to the state of
technology envisioned in the
airworthiness standards for transportcategory airplanes. This design feature
is seats with non-traditional, large, nonmetallic panels. The applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for this design feature. These special
conditions contain the additional safety
standards that the Administrator
considers necessary to establish a level
of safety equivalent to that established
by the existing airworthiness standards.
SUMMARY:
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29JYR1
49872
Federal Register / Vol. 81, No. 146 / Friday, July 29, 2016 / Rules and Regulations
This action is effective on ATR
on July 29, 2016. We must receive your
comments by September 12, 2016.
ADDRESSES: Send comments identified
by docket number FAA–2016–8246
using any of the following methods:
• Federal eRegulations Portal: Go to
https://www.regulations.gov/and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to Docket
Operations, M–30, U.S. Department of
Transportation (DOT), 1200 New Jersey
Avenue SE., Room W12–140, West
Building Ground Floor, Washington, DC
20590–0001.
• Hand Delivery or Courier: Take
comments to Docket Operations in
Room W12–140 of the West Building
Ground Floor at 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• Fax: Fax comments to Docket
Operations at 202–493–2251.
Privacy: The FAA will post all
comments it receives, without change,
to https://www.regulations.gov/,
including any personal information the
commenter provides. Using the search
function of the docket Web site, anyone
can find and read the electronic form of
all comments received into any FAA
docket, including the name of the
individual sending the comment (or
signing the comment for an association,
business, labor union, etc.). DOT’s
complete Privacy Act Statement can be
found in the Federal Register published
on April 11, 2000 (65 FR 19477–19478),
as well as at https://DocketsInfo.dot
.gov/.
Docket: Background documents or
comments received may be read at
https://www.regulations.gov/ at any time.
Follow the online instructions for
accessing the docket or go to Docket
Operations in Room W12–140 of the
West Building Ground Floor at 1200
New Jersey Avenue SE., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: John
Shelden, Airframe and Cabin Safety,
ANM–115, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356;
telephone 425–227–2785; facsimile
425–227–1149.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice of, and
opportunity for prior public comment
on, these special conditions is
impracticable because these procedures
would significantly delay issuance of
the design approval, and thus delivery,
of the affected airplanes.
asabaliauskas on DSK3SPTVN1PROD with RULES
DATES:
VerDate Sep<11>2014
17:52 Jul 28, 2016
Jkt 238001
In addition, the substance of these
special conditions has been subject to
the public-comment process in several
prior instances with no substantive
comments received. The FAA therefore
finds that good cause exists for making
these special conditions effective upon
publication in the Federal Register.
Comments Invited
We invite interested people to take
part in this rulemaking by sending
written comments, data, or views. The
most helpful comments reference a
specific portion of the special
conditions, explain the reason for any
recommended change, and include
supporting data.
We will consider all comments we
receive by the closing date for
comments. We may change these special
conditions based on the comments we
receive.
Background
On March 2, 2016, ATR applied for a
change to type certificate no. A53EU for
the installation of seats constructed of
non-traditional, non-metallic materials
in the Model ATR–42–200/–300/–320/–
500, and ATR–72–102/–202/–212/–
212A airplanes.
The Model ATR–42/–72 series
airplanes are twin-engine,
turbopropeller-powered, transportcategory airplanes with maximum
passenger capacity up to 74, depending
upon airplane model.
Type Certification Basis
Under the provisions of Title 14, Code
of Federal Regulations (14 CFR) 21.101,
ATR must show that the Model ATR–
42–200/–300/–320/–500 and ATR–72–
102/–202/–212/–212A airplanes, as
changed, continue to meet the
applicable provisions of the regulations
listed in type certificate no. A53EU, or
the applicable regulations in effect on
the date of application for the change,
except for earlier amendments as agreed
upon by the FAA.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., 14 CFR part 25) do not contain
adequate or appropriate safety standards
for the Model ATR–42–200/–300/–320/
–500 and ATR–72–102/–202/–212/–
212A airplanes because of a novel or
unusual design feature, special
conditions are prescribed under the
provisions of § 21.16.
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
include any other model that
incorporates the same novel or unusual
design feature, or should any other
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
model already included on the same
type certificate be modified to
incorporate the same novel or unusual
design feature, these special conditions
would also apply to the other model
under § 21.101.
In addition to the applicable
airworthiness regulations and special
conditions, the Model ATR–42–200/–
300/–320/–500 and ATR–72–102/–202/
–212/–212A airplanes must comply
with the fuel-vent and exhaust-emission
requirements of 14 CFR part 34, and the
noise-certification requirements of 14
CFR part 36.
The FAA issues special conditions, as
defined in 14 CFR 11.19, in accordance
with § 11.38, and they become part of
the type certification basis under
§ 21.101.
Novel or Unusual Design Features
The Model ATR–42–200/–300/–320/–
500 and ATR–72–102/–202/–212/–212A
airplanes will incorporate the following
novel or unusual design feature:
Passenger seats that incorporate nontraditional, large, non-metallic panels in
lieu of the traditional metal frame
covered by fabric.
Discussion
In the early 1980s, the FAA
conducted extensive research on the
effects of post-crash flammability in the
passenger cabin. As a result of this
research and service experience, the
FAA adopted new standards for interior
surfaces associated with large surfacearea parts. Specifically, the rules require
measurement of heat release and smoke
emission (part 25, Appendix F, parts IV
and V) for the affected parts. Heat
release has been shown to have a direct
correlation with post- crash-fire survival
time. Materials that comply with the
standards (i.e., § 25.853, ‘‘Compartment
interiors’’ at Amendment 25–61 and
Amendment 25–66) extend survival
time by approximately 2 minutes over
materials that do not comply.
At the time these standards were
written, the potential application of the
requirements of seat heat release and
smoke emission was explored. The seat
frame itself was not a concern because
it was primarily made of aluminum and
only small amounts of non-metallic
materials. Research determined that the
overall effect on survivability was
negligible, whether or not the food trays
met the heat-release and smokeemission requirements. The
requirements therefore did not address
seats. The preambles to both the Notice
of Proposed Rule Making (NPRM),
Notice No. 85–10 (50 FR 15038, April
16, 1985), and the Final Rule at
Amendment 25–61 (51 FR 26206, July
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29JYR1
asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 146 / Friday, July 29, 2016 / Rules and Regulations
21, 1986), specifically note that seats
were excluded ‘‘because the recently
adopted standards for flammability of
seat cushions will greatly inhibit
involvement of the seats.’’
Subsequently, the Final Rule at
Amendment 25–83 (60 FR 6615, March
6, 1995) clarified the definition of
minimum panel size: ‘‘It is not possible
to cite a specific size that will apply in
all installations; however, as a general
rule, components with exposed surface
areas of one square foot or less may be
considered small enough that they do
not have to meet the new standards.
Components with exposed surface areas
greater than two square feet may be
considered large enough that they do
have to meet the new standards. Those
with exposed surface areas greater than
one square foot, but less than two square
feet, must be considered in conjunction
with the areas of the cabin in which
they are installed before a determination
could be made.’’
In the late 1990s, the FAA issued
Policy Memorandum 97–112–39,
‘‘Guidance for Flammability Testing of
Seat/Console Installations,’’ October 17,
1997 (https://rgl.faa.gov). That memo
was issued when it became clear that
seat designs were evolving to include
large, non-metallic panels with surface
areas that would impact survivability
during a cabin-fire event, comparable to
partitions or galleys. The memo noted
that large-surface-area panels must
comply with heat-release and smokeemission requirements, even if they
were attached to a seat. If the FAA had
not issued such policy, seat designs
could have been viewed as a loophole
to the airworthiness standards that
would result in an unacceptable
decrease in survivability during a cabinfire event.
In October of 2004, an issue was
raised regarding the appropriate
flammability standards for passenger
seats that incorporated non-traditional,
large, non-metallic panels in lieu of the
traditional metal covered by fabric. The
FAA Seattle Aircraft Certification Office
and Transport Standards Staff reviewed
this design, and determined that it
represented the kind and quantity of
material that should be required to pass
the heat-release and smoke-emissions
requirements. The FAA has determined
that special conditions would be issued
to apply the standards defined in 14
CFR 25.853(d) to seats with large, nonmetallic panels in their design.
Traditional seat panels would not be
covered by the special conditions.
These special conditions contain the
additional safety standards that the
Administrator considers necessary to
establish a level of safety equivalent to
VerDate Sep<11>2014
17:04 Jul 28, 2016
Jkt 238001
that established by the existing
airworthiness standards.
Applicability
As discussed above, these special
conditions are applicable to the Model
ATR–42–200/–300/–320/–500 and
ATR–72–102/–202/–212/–212A
airplanes. Should ATR apply at a later
date for a change to the type certificate
to include another model incorporating
the same novel or unusual design
feature, these special conditions would
apply to that model as well. These
special conditions apply to new seatcertification programs. Previously
approved seats are not affected by these
special conditions.
Conclusion
This action affects only certain novel
or unusual design features on two
model series of airplanes. It is not a rule
of general applicability.
The substance of these special
conditions has been subjected to the
notice and comment period in several
prior instances and has been derived
without substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. Therefore, because a
delay would significantly affect the
certification of the airplane, which is
imminent, the FAA has determined that
prior public notice and comment are
unnecessary and impracticable, and
good cause exists for adopting these
special conditions upon publication in
the Federal Register. The FAA is
requesting comments to allow interested
persons to submit views that may not
have been submitted in response to the
prior opportunities for comment
described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for ATR Model ATR–
42–200/–300/–320/–500 and ATR–72–
102/–202/–212/–212A airplanes for new
seat-certification programs.
1. Compliance with 14 CFR part 25
Appendix F, parts IV and V, ‘‘Heat
release and smoke emission,’’ is
required for seats that incorporate nontraditional, large, non-metallic panels
PO 00000
Frm 00019
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49873
that may be either a single component
or multiple components in a
concentrated area in their design.
2. The applicant may designate up to
and including 1.5 square feet of nontraditional, non-metallic panel material
per seat place that does not have to
comply with special condition 1, above.
A triple seat assembly may have a total
of 4.5 square feet excluded on any
portion of the assembly (e.g., outboard
seat place, 1 sq. ft.; middle, 1 sq. ft.; and
inboard, 2.5 sq. ft.)
3. Seats need not meet the test
requirements of 14 CFR part 25
Appendix F, parts IV and V, when
installed in compartments that are not
otherwise required to meet these
requirements. Examples include
airplanes:
a. With passenger capacities of 19 or
fewer;
b. that do not have smoke-emission
and heat-release test requirements in
their certification basis, and that are not
required by 14 CFR 121.312 to conduct
such tests; or
c. that are exempted from smokeemission and heat-release testing.
Issued in Renton, Washington, on July 21,
2016.
Michael Kaszycki,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–17846 Filed 7–28–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3700; Directorate
Identifier 2015–NM–171–AD; Amendment
39–18595; AD 2016–15–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757–200 and
–200CB series airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that the lap splices at stringer
S–14R, lower fastener row, are subject to
widespread fatigue damage (WFD). This
AD requires external dual frequency
eddy current (DFEC) or internal high
frequency eddy current (HFEC)
inspections of the lap splice, inner skin
SUMMARY:
E:\FR\FM\29JYR1.SGM
29JYR1
]]>Agencies
[Federal Register Volume 81, Number 146 (Friday, July 29, 2016)]
[Rules and Regulations]
[Pages 49871-49873]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-17846]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2016-8246; Special Conditions No. 25-624-SC]
Special Conditions: ATR Model ATR-42-200/-300/-320/-500 and ATR-
72-102/-202/-212/-212A Airplanes; Seats With Non-Traditional, Large,
Non-Metallic Panels
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for ATR Model ATR-42-200/-
300/-320/-500 and ATR-72-102/-202/-212/-212A airplanes. These airplanes
will have a novel or unusual design feature when compared to the state
of technology envisioned in the airworthiness standards for transport-
category airplanes. This design feature is seats with non-traditional,
large, non-metallic panels. The applicable airworthiness regulations do
not contain adequate or appropriate safety standards for this design
feature. These special conditions contain the additional safety
standards that the Administrator considers necessary to establish a
level of safety equivalent to that established by the existing
airworthiness standards.
[[Page 49872]]
DATES: This action is effective on ATR on July 29, 2016. We must
receive your comments by September 12, 2016.
ADDRESSES: Send comments identified by docket number FAA-2016-8246
using any of the following methods:
Federal eRegulations Portal: Go to https://www.regulations.gov/and follow the online instructions for sending your
comments electronically.
Mail: Send comments to Docket Operations, M-30, U.S.
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
Hand Delivery or Courier: Take comments to Docket
Operations in Room W12-140 of the West Building Ground Floor at 1200
New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Fax: Fax comments to Docket Operations at 202-493-2251.
Privacy: The FAA will post all comments it receives, without
change, to https://www.regulations.gov/, including any personal
information the commenter provides. Using the search function of the
docket Web site, anyone can find and read the electronic form of all
comments received into any FAA docket, including the name of the
individual sending the comment (or signing the comment for an
association, business, labor union, etc.). DOT's complete Privacy Act
Statement can be found in the Federal Register published on April 11,
2000 (65 FR 19477-19478), as well as at https://DocketsInfo.dot.gov/.
Docket: Background documents or comments received may be read at
https://www.regulations.gov/ at any time. Follow the online instructions
for accessing the docket or go to Docket Operations in Room W12-140 of
the West Building Ground Floor at 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.
FOR FURTHER INFORMATION CONTACT: John Shelden, Airframe and Cabin
Safety, ANM-115, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone
425-227-2785; facsimile 425-227-1149.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and
opportunity for prior public comment on, these special conditions is
impracticable because these procedures would significantly delay
issuance of the design approval, and thus delivery, of the affected
airplanes.
In addition, the substance of these special conditions has been
subject to the public-comment process in several prior instances with
no substantive comments received. The FAA therefore finds that good
cause exists for making these special conditions effective upon
publication in the Federal Register.
Comments Invited
We invite interested people to take part in this rulemaking by
sending written comments, data, or views. The most helpful comments
reference a specific portion of the special conditions, explain the
reason for any recommended change, and include supporting data.
We will consider all comments we receive by the closing date for
comments. We may change these special conditions based on the comments
we receive.
Background
On March 2, 2016, ATR applied for a change to type certificate no.
A53EU for the installation of seats constructed of non-traditional,
non-metallic materials in the Model ATR-42-200/-300/-320/-500, and ATR-
72-102/-202/-212/-212A airplanes.
The Model ATR-42/-72 series airplanes are twin-engine,
turbopropeller-powered, transport-category airplanes with maximum
passenger capacity up to 74, depending upon airplane model.
Type Certification Basis
Under the provisions of Title 14, Code of Federal Regulations (14
CFR) 21.101, ATR must show that the Model ATR-42-200/-300/-320/-500 and
ATR-72-102/-202/-212/-212A airplanes, as changed, continue to meet the
applicable provisions of the regulations listed in type certificate no.
A53EU, or the applicable regulations in effect on the date of
application for the change, except for earlier amendments as agreed
upon by the FAA.
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 25) do not contain adequate or
appropriate safety standards for the Model ATR-42-200/-300/-320/-500
and ATR-72-102/-202/-212/-212A airplanes because of a novel or unusual
design feature, special conditions are prescribed under the provisions
of Sec. 21.16.
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates the same novel or
unusual design feature, or should any other model already included on
the same type certificate be modified to incorporate the same novel or
unusual design feature, these special conditions would also apply to
the other model under Sec. 21.101.
In addition to the applicable airworthiness regulations and special
conditions, the Model ATR-42-200/-300/-320/-500 and ATR-72-102/-202/-
212/-212A airplanes must comply with the fuel-vent and exhaust-emission
requirements of 14 CFR part 34, and the noise-certification
requirements of 14 CFR part 36.
The FAA issues special conditions, as defined in 14 CFR 11.19, in
accordance with Sec. 11.38, and they become part of the type
certification basis under Sec. 21.101.
Novel or Unusual Design Features
The Model ATR-42-200/-300/-320/-500 and ATR-72-102/-202/-212/-212A
airplanes will incorporate the following novel or unusual design
feature:
Passenger seats that incorporate non-traditional, large, non-
metallic panels in lieu of the traditional metal frame covered by
fabric.
Discussion
In the early 1980s, the FAA conducted extensive research on the
effects of post-crash flammability in the passenger cabin. As a result
of this research and service experience, the FAA adopted new standards
for interior surfaces associated with large surface-area parts.
Specifically, the rules require measurement of heat release and smoke
emission (part 25, Appendix F, parts IV and V) for the affected parts.
Heat release has been shown to have a direct correlation with post-
crash-fire survival time. Materials that comply with the standards
(i.e., Sec. 25.853, ``Compartment interiors'' at Amendment 25-61 and
Amendment 25-66) extend survival time by approximately 2 minutes over
materials that do not comply.
At the time these standards were written, the potential application
of the requirements of seat heat release and smoke emission was
explored. The seat frame itself was not a concern because it was
primarily made of aluminum and only small amounts of non-metallic
materials. Research determined that the overall effect on survivability
was negligible, whether or not the food trays met the heat-release and
smoke-emission requirements. The requirements therefore did not address
seats. The preambles to both the Notice of Proposed Rule Making (NPRM),
Notice No. 85-10 (50 FR 15038, April 16, 1985), and the Final Rule at
Amendment 25-61 (51 FR 26206, July
[[Page 49873]]
21, 1986), specifically note that seats were excluded ``because the
recently adopted standards for flammability of seat cushions will
greatly inhibit involvement of the seats.''
Subsequently, the Final Rule at Amendment 25-83 (60 FR 6615, March
6, 1995) clarified the definition of minimum panel size: ``It is not
possible to cite a specific size that will apply in all installations;
however, as a general rule, components with exposed surface areas of
one square foot or less may be considered small enough that they do not
have to meet the new standards. Components with exposed surface areas
greater than two square feet may be considered large enough that they
do have to meet the new standards. Those with exposed surface areas
greater than one square foot, but less than two square feet, must be
considered in conjunction with the areas of the cabin in which they are
installed before a determination could be made.''
In the late 1990s, the FAA issued Policy Memorandum 97-112-39,
``Guidance for Flammability Testing of Seat/Console Installations,''
October 17, 1997 (https://rgl.faa.gov). That memo was issued when it
became clear that seat designs were evolving to include large, non-
metallic panels with surface areas that would impact survivability
during a cabin-fire event, comparable to partitions or galleys. The
memo noted that large-surface-area panels must comply with heat-release
and smoke-emission requirements, even if they were attached to a seat.
If the FAA had not issued such policy, seat designs could have been
viewed as a loophole to the airworthiness standards that would result
in an unacceptable decrease in survivability during a cabin-fire event.
In October of 2004, an issue was raised regarding the appropriate
flammability standards for passenger seats that incorporated non-
traditional, large, non-metallic panels in lieu of the traditional
metal covered by fabric. The FAA Seattle Aircraft Certification Office
and Transport Standards Staff reviewed this design, and determined that
it represented the kind and quantity of material that should be
required to pass the heat-release and smoke-emissions requirements. The
FAA has determined that special conditions would be issued to apply the
standards defined in 14 CFR 25.853(d) to seats with large, non-metallic
panels in their design. Traditional seat panels would not be covered by
the special conditions.
These special conditions contain the additional safety standards
that the Administrator considers necessary to establish a level of
safety equivalent to that established by the existing airworthiness
standards.
Applicability
As discussed above, these special conditions are applicable to the
Model ATR-42-200/-300/-320/-500 and ATR-72-102/-202/-212/-212A
airplanes. Should ATR apply at a later date for a change to the type
certificate to include another model incorporating the same novel or
unusual design feature, these special conditions would apply to that
model as well. These special conditions apply to new seat-certification
programs. Previously approved seats are not affected by these special
conditions.
Conclusion
This action affects only certain novel or unusual design features
on two model series of airplanes. It is not a rule of general
applicability.
The substance of these special conditions has been subjected to the
notice and comment period in several prior instances and has been
derived without substantive change from those previously issued. It is
unlikely that prior public comment would result in a significant change
from the substance contained herein. Therefore, because a delay would
significantly affect the certification of the airplane, which is
imminent, the FAA has determined that prior public notice and comment
are unnecessary and impracticable, and good cause exists for adopting
these special conditions upon publication in the Federal Register. The
FAA is requesting comments to allow interested persons to submit views
that may not have been submitted in response to the prior opportunities
for comment described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for ATR Model ATR-42-200/-300/-320/-500
and ATR-72-102/-202/-212/-212A airplanes for new seat-certification
programs.
1. Compliance with 14 CFR part 25 Appendix F, parts IV and V,
``Heat release and smoke emission,'' is required for seats that
incorporate non-traditional, large, non-metallic panels that may be
either a single component or multiple components in a concentrated area
in their design.
2. The applicant may designate up to and including 1.5 square feet
of non-traditional, non-metallic panel material per seat place that
does not have to comply with special condition 1, above. A triple seat
assembly may have a total of 4.5 square feet excluded on any portion of
the assembly (e.g., outboard seat place, 1 sq. ft.; middle, 1 sq. ft.;
and inboard, 2.5 sq. ft.)
3. Seats need not meet the test requirements of 14 CFR part 25
Appendix F, parts IV and V, when installed in compartments that are not
otherwise required to meet these requirements. Examples include
airplanes:
a. With passenger capacities of 19 or fewer;
b. that do not have smoke-emission and heat-release test
requirements in their certification basis, and that are not required by
14 CFR 121.312 to conduct such tests; or
c. that are exempted from smoke-emission and heat-release testing.
Issued in Renton, Washington, on July 21, 2016.
Michael Kaszycki,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2016-17846 Filed 7-28-16; 8:45 am]
BILLING CODE 4910-13-P
