Special Conditions: Bombardier Inc. Model BD-700-2A12 and BD-700-2A13 Airplanes; Fuselage In-Flight Fire Safety and Flammability Resistance of Aluminum-Lithium Material, 17531-17533 [2017-07326]
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17531
Rules and Regulations
Federal Register
Vol. 82, No. 69
Wednesday, April 12, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF AGRICULTURE
Grain Inspection, Packers and
Stockyards Administration
9 CFR Part 201
RIN 0580–AB25
Scope of Sections 202(a) and (b) of the
Packers and Stockyards Act
Grain Inspection, Packers and
Stockyards Administration, USDA.
ACTION: Interim final rule; notice of
delay of effective date.
AGENCY:
The United States Department
of Agriculture’s (USDA) Grain
Inspection, Packers and Stockyards
Administration (GIPSA) is delaying the
effective date of the rule published on
December 20, 2016, for an additional six
months to October 19, 2017, in response
to a comment received from a national
general farm organization that requested
an extension of time and to allow time
for further consideration by USDA. The
effective date for this rule was originally
February 21, 2017, and subsequently
delayed to April 22, 2017, by a
document published in the Federal
Register on February 7, 2017. The
interim final rule addresses the scope of
sections 202(a) and (b) of the Packers
and Stockyards Act, 1921, as amended
and supplemented (P&S Act) in order to
clarify that conduct or action may
violate sections 202(a) and (b) of the
P&S Act without adversely affecting, or
having a likelihood of adversely
affecting, competition.
DATES: The effective date for the interim
final rule amending 9 CFR part 201,
published at 81 FR 92566, December 20,
2016, delayed at 82 FR 9489, February
7, 2017, is further delayed until October
19, 2017.
FOR FURTHER INFORMATION CONTACT: S.
Brett Offutt, Director, Litigation and
Economic Analysis Division, P&SP,
GIPSA, 1400 Independence Ave. SW.,
Washington, DC 20250, (202) 720–7051,
s.brett.offutt@usda.gov.
pmangrum on DSK3GDR082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
15:14 Apr 11, 2017
Jkt 241001
Consistent
with the memorandum of January 20,
2017, to the heads of executive
departments and agencies from the
Assistant to the President and Chief of
Staff entitled ‘‘Regulatory Freeze
Pending Review,’’ on February 7, 2017,
GIPSA extended the public comment
period and delayed the effective date of
the interim final rule entitled ‘‘Scope of
sections 202(a) and (b) of the Packers
and Stockyards Act’’ that was published
in the Federal Register on December 20,
2016, 81 FR 92566. The comment period
was extended at that time to March 24,
2017, and the effective date delayed to
April 22, 2017.
Given the significant public interest
in this rule, GIPSA has found that the
initial delay of the effective date to
April 22, 2017, will likely not provide
sufficient time for USDA to adequately
consider all comments received and
make informed policy decisions
regarding this rule. GIPSA is therefore
further delaying the effective date of this
rule an additional 180 days to October
19, 2017. In addition, GIPSA will
publish a proposed rule that solicits
public comments on the direction that
USDA should take with respect to the
rule. The public will have a 60-day
comment period to specify whether
USDA should (1) let the rule become
effective, (2) suspend the rule
indefinitely, (3) delay the effective date
of the rule further, or (4) withdraw the
rule.
As published, this interim final rule
states the USDA’s long held
interpretation that not all violations of
the P&S Act require a showing of harm
or likely harm to competition. Section
201.3(a) specifically provides that the
scope of section 202(a) and (b)
encompasses conduct or action that,
depending on their nature and the
circumstances, can be found to violate
the P&S Act without a finding of harm
or likely harm to competition. This
interim final rule finalizes a proposed
§ 201.3(c) that GIPSA published on June
22, 2010, 75 FR 35338, with slight
modifications in order to allow
additional public comment on these
provisions.
To the extent that 5 U.S.C. 553(b)(A)
applies to this action, it is exempt from
notice and comment rulemaking for
good cause and for reasons cited above,
GIPSA finds that notice and solicitation
of comment regarding the extension of
SUPPLEMENTARY INFORMATION:
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Frm 00001
Fmt 4700
Sfmt 4700
the effective date of the interim final
rule are impracticable, unnecessary, or
contrary to the public interest pursuant
to 5 U.S.C. 553(b)(B). The delay of the
effective date until October 19, 2017,
should give GIPSA sufficient time to
receive and consider public comments
and to take action on the disposition of
the IFR. Delaying the effective date
would also reduce confusion or
uncertainty for the industry while
GIPSA determines the appropriate final
disposition of the IFR. GIPSA believes
that affected parties need to be informed
as soon as possible of the extension and
its length.
Randall D. Jones,
Acting Administrator, Grain Inspection,
Packers and Stockyards Administration.
[FR Doc. 2017–07360 Filed 4–11–17; 8:45 am]
BILLING CODE 3410–KD–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2016–4158; Special
Conditions No. 25–656–SC]
Special Conditions: Bombardier Inc.
Model BD–700–2A12 and BD–700–
2A13 Airplanes; Fuselage In-Flight Fire
Safety and Flammability Resistance of
Aluminum-Lithium Material
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
These special conditions are
issued for the Bombardier Inc.
(Bombardier) Model BD–700–2A12 and
BD–700–2A13 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 a fuselage fabricated using aluminumlithium materials instead of
conventional aluminum. The applicable
airworthiness regulations do not contain
adequate or appropriate fire-safety
standards for this design feature. These
special conditions contain the
additional fire-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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12APR1
17532
DATES:
Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
Effective May 12, 2017.
FOR FURTHER INFORMATION CONTACT:
Alan Sinclair, FAA, Airframe and Cabin
Safety Branch, ANM–115, Transport
Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue
SW., Renton, Washington, 98057–3356;
telephone 425–227–2195; facsimile
425–227–1320.
SUPPLEMENTARY INFORMATION:
Background
On May 30, 2012, Bombardier applied
for an amendment to Type Certificate
No. T00003NY to include the new
Model BD–700–2A12 and BD–700–
2A13 airplanes. These airplanes are
derivatives of the Model BD–700 series
of airplanes and are marketed as the
Bombardier Global 7000 (Model BD–
700–2A12) and Global 8000 (Model BD–
700–2A13). These airplanes are twinengine, transport-category, executiveinterior business jets. The maximum
passenger capacity is 19 and the
maximum takeoff weights are 106,250
lb. (Model BD–700–2A12) and 104,800
lb. (Model BD–700–2A13).
pmangrum on DSK3GDR082PROD with RULES
Type Certification Basis
Under the provisions of Title 14, Code
of Federal Regulations (14 CFR) 21.101,
Bombardier must show that the Model
BD–700–2A12 and BD–700–2A13
airplanes meet the applicable provisions
of the regulations listed in Type
Certificate No. T00003NY, or the
applicable regulations in effect on the
date of application for the change,
except for earlier amendments as agreed
upon by the FAA.
In addition, the certification basis
includes other regulations, special
conditions, and exemptions that are not
relevant to these special conditions.
Type Certificate No. T00003NY will be
updated to include a complete
description of the certification basis for
these airplane models.
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 BD–700–2A12 and BD–
700–2A13 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
model already included on the same
type certificate be modified to
incorporate the same novel or unusual
VerDate Sep<11>2014
15:14 Apr 11, 2017
Jkt 241001
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 BD–700–2A12
and BD–700–2A13 airplanes must
comply with the fuel-vent and exhaustemission 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 Feature
Bombardier Model BD–700–2A12 and
BD–700–2A13 airplanes will
incorporate the following novel or
unusual design feature: The fuselage
will be fabricated using aluminumlithium alloy materials instead of
conventional aluminum.
Discussion
The Bombardier Model BD–700–2A12
and BD–700–2A13 airplanes will be
fabricated using aluminum-lithium
materials. The performance of airplanes
consisting of a conventional aluminum
fuselage, in an in-flight, inaccessible-fire
scenario, is understood based on service
history, and extensive intermediate- and
large-scale fire testing. Experience has
shown that eliminating fire propagation
of the interior and insulation materials
tends to increase survivability because
other aspects of in-flight fire safety (e.g.,
toxic-gas emission and smoke
obscuration) are typically byproducts of
the propagating fire. The fuselage itself
does not contribute to in-flight fire
propagation. This may not be the case
for a fuselage fabricated from
aluminum-lithium materials. Therefore,
special conditions are necessary so that
the Model BD–700–2A12 and BD–700–
2A13 airplanes provide protection
against in-flight fires propagating along
the surface of the fuselage.
In the past, fatal in-flight fires have
originated in inaccessible areas of
airplanes where thermal or acoustic
insulation was located adjacent to the
airplane’s aluminum fuselage skin.
Research revealed that this area has
been the path for flame propagation and
fire growth. The FAA determined, in
five incidents in the 1990s, that
unexpected flame spread along thermal
and acoustic insulation-film covering
material, raising concerns about the fire
performance of this material. In all
cases, the ignition source was relatively
modest and, in most cases, was
electrical in origin (e.g., electrical short
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
circuit, arcing caused by chafed wiring,
ruptured ballast case, etc.).
In 1996, the FAA Technical Center
began a program to develop new fire-test
criteria for insulation films directly
relating to in-flight fire resistance. This
development program resulted in a new
test method—the radiant-panel test—
and also resulted in test criteria
specifically established for improving
the in-flight fire ignition and flame
propagation of thermal and acoustic
insulation materials based on actual, onboard fire scenarios.
The FAA determined that a test
similar to the test for the measurement
of insulation burnthrough resistance (14
CFR part 25, Appendix F, Part VII, ‘‘Test
Method to Determine the Burnthrough
Resistance of Thermal/Acoustic
Insulation Materials’’) could be used to
assess the flammability characteristics
of the proposed fuselage aluminumlithium material. The only change to the
test is the size of the sample and the
sample holder, to accommodate panels
of the fuselage material.
Bombardier must use the test method
contained in Part VII of Appendix F,
Test Method, for determining the
burnthrough resistance of thermalacoustic insulation materials, with the
slight changes to the sample size and
sample holder, as described in these
special conditions, to show that the
aluminum-lithium material complies
with applicable requirements.
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.
Discussion of Comments
Notice of Proposed Special
Conditions No. 25–16–06–SC for the
Bombardier Model BD–700–2A12 and
BD–700–2A11 airplanes was published
in the Federal Register on October 26,
2016 (81 FR 74348). One comment was
received.
The commenter acknowledged that
the use of the aluminum-lithium alloy
would require full certification to the
existing regulations. However, they
contend that the material is not novel
and unusual and does not require
special conditions.
The FAA does not agree. While it is
true that, with materials presently
tested, the proposed aluminum-lithium
alloy does not appear to pose a
significant risk, the existing regulations
and guidance do not adequately address
the use of this specific alloy technology.
Therefore, special conditions are
required until the regulations are
amended to provide sufficient
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12APR1
Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
requirements for the application of this
new alloy technology.
Applicability
As discussed above, these special
conditions are applicable to Bombardier
Model BD–700–2A12 and BD–700–
2A13 airplanes. Should Bombardier
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 the other
model as well.
Conclusion
This action affects only a certain
novel or unusual design feature on
Bombardier Model BD–700–2A12 and
BD–700–2A13 airplanes. It is not a rule
of general applicability and affects only
the applicant who applied to FAA for
approval of this feature on the airplane.
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:
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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 Bombardier Model BD–700–
2A12 and BD–700–2A13 airplanes.
1. Bombardier must demonstrate that
the aluminum-lithium material has
equal or better flammability-resistance
characteristics than the aluminum-alloy
sheet material typically used as skin
material on similar airplanes.
2. The test set-up and methodology
must be in accordance with the tests
described in 14 CFR part 25, Appendix
F, Part VII, except for the following.
a. Each test sample must consist of a
flat test specimen. A set of three
samples of aluminum-lithium sheet
material must be tested. The size of each
sample must be 16 inches wide by 24
inches long by 0.063 inch thick.
b. The test samples must be installed
into a steel-sheet subframe with outside
dimensions of 18 inches by 32 inches.
The subframe must have a 14.5-inch by
22.5-inch opening cut into it. The tests
samples must be mounted onto the
subframe using 0.250–20 UNC threaded
bolts.
c. Test specimens must be
conditioned at 70 °F + 5 °F, and 55%
+ 5% humidity, for at least 24 hours
before testing.
3. The aluminum-lithium material
must not ignite during any of the tests.
15:14 Apr 11, 2017
Jkt 241001
[FR Doc. 2017–07326 Filed 4–11–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0651; Directorate
Identifier 2014–NM–043–AD; Amendment
39–18850; AD 2017–08–01]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace Corporation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–22–
19 for all Gulfstream Aerospace
Corporation Model GV and GV–SP
airplanes. AD 2013–22–19 required
inspecting to determine if fuel boost
pumps having a certain part number
were installed, replacing the fuel boost
pumps having a certain part number,
and revising the airplane maintenance
program to include revised Instructions
for Continued Airworthiness. This new
AD reduces the compliance time for
revising the airplane maintenance or
inspection program. This AD was
prompted by reports of two independent
types of failure of the fuel boost pump
with overheat damage found on the
internal components and external
housing on one of the failure types, and
fuel leakage on the other. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective May 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 17, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 7, 2014 (78 FR
72554, December 3, 2013).
ADDRESSES: For Gulfstream, Triumph
Aerostructures, and General Electric
Aviation service information identified
in this final rule, contact Gulfstream
Aerospace Corporation, Technical
Publications Dept., P.O. Box 2206,
Savannah, GA 31402–2206; telephone
800–810–4853; fax 912 965–3520; email
SUMMARY:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
VerDate Sep<11>2014
Issued in Renton, Washington, on April 3,
2017.
Michael Kaszycki,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
17533
pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0651.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0651; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Ky
Phan, Aerospace Engineer, Propulsion
and Services Branch, ACE–118A, FAA,
Atlanta ACO, 1701 Columbia Avenue,
College Park, GA 30337; phone: 404–
474–5536; fax: 404–474–5606; email:
ky.phan@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2013–22–19, Amendment 39–17651 (78
FR 72554, December 3, 2013) (‘‘AD
2013–22–19’’). AD 2013–22–19 applied
to all Gulfstream Aerospace Corporation
Model GV and GV–SP airplanes. The
SNPRM published in the Federal
Register on December 24, 2015 (80 FR
80295). We preceded the SNPRM with
a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on October 1, 2014 (79 FR
59162) (‘‘the NPRM’’). The NPRM
proposed to supersede AD 2013–22–19.
The NPRM was prompted by reports of
two independent types of failure of the
fuel boost pump with overheat damage
on the internal components and external
housing on one of the failure types, and
fuel leakage on the other. The SNPRM
proposed to reduce the compliance time
for revising the airplane maintenance or
inspection program. We are issuing this
E:\FR\FM\12APR1.SGM
12APR1
]]>Agencies
[Federal Register Volume 82, Number 69 (Wednesday, April 12, 2017)]
[Rules and Regulations]
[Pages 17531-17533]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07326]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2016-4158; Special Conditions No. 25-656-SC]
Special Conditions: Bombardier Inc. Model BD-700-2A12 and BD-700-
2A13 Airplanes; Fuselage In-Flight Fire Safety and Flammability
Resistance of Aluminum-Lithium Material
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Bombardier Inc.
(Bombardier) Model BD-700-2A12 and BD-700-2A13 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 a fuselage
fabricated using aluminum-lithium materials instead of conventional
aluminum. The applicable airworthiness regulations do not contain
adequate or appropriate fire-safety standards for this design feature.
These special conditions contain the additional fire-safety standards
that the Administrator considers necessary to establish a level of
safety equivalent to that established by the existing airworthiness
standards.
[[Page 17532]]
DATES: Effective May 12, 2017.
FOR FURTHER INFORMATION CONTACT: Alan Sinclair, FAA, Airframe and Cabin
Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98057-
3356; telephone 425-227-2195; facsimile 425-227-1320.
SUPPLEMENTARY INFORMATION:
Background
On May 30, 2012, Bombardier applied for an amendment to Type
Certificate No. T00003NY to include the new Model BD-700-2A12 and BD-
700-2A13 airplanes. These airplanes are derivatives of the Model BD-700
series of airplanes and are marketed as the Bombardier Global 7000
(Model BD-700-2A12) and Global 8000 (Model BD-700-2A13). These
airplanes are twin-engine, transport-category, executive-interior
business jets. The maximum passenger capacity is 19 and the maximum
takeoff weights are 106,250 lb. (Model BD-700-2A12) and 104,800 lb.
(Model BD-700-2A13).
Type Certification Basis
Under the provisions of Title 14, Code of Federal Regulations (14
CFR) 21.101, Bombardier must show that the Model BD-700-2A12 and BD-
700-2A13 airplanes meet the applicable provisions of the regulations
listed in Type Certificate No. T00003NY, or the applicable regulations
in effect on the date of application for the change, except for earlier
amendments as agreed upon by the FAA.
In addition, the certification basis includes other regulations,
special conditions, and exemptions that are not relevant to these
special conditions. Type Certificate No. T00003NY will be updated to
include a complete description of the certification basis for these
airplane models.
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 BD-700-2A12 and BD-700-2A13
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 BD-700-2A12 and BD-700-2A13 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 Feature
Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes will
incorporate the following novel or unusual design feature: The fuselage
will be fabricated using aluminum-lithium alloy materials instead of
conventional aluminum.
Discussion
The Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes will be
fabricated using aluminum-lithium materials. The performance of
airplanes consisting of a conventional aluminum fuselage, in an in-
flight, inaccessible-fire scenario, is understood based on service
history, and extensive intermediate- and large-scale fire testing.
Experience has shown that eliminating fire propagation of the interior
and insulation materials tends to increase survivability because other
aspects of in-flight fire safety (e.g., toxic-gas emission and smoke
obscuration) are typically byproducts of the propagating fire. The
fuselage itself does not contribute to in-flight fire propagation. This
may not be the case for a fuselage fabricated from aluminum-lithium
materials. Therefore, special conditions are necessary so that the
Model BD-700-2A12 and BD-700-2A13 airplanes provide protection against
in-flight fires propagating along the surface of the fuselage.
In the past, fatal in-flight fires have originated in inaccessible
areas of airplanes where thermal or acoustic insulation was located
adjacent to the airplane's aluminum fuselage skin. Research revealed
that this area has been the path for flame propagation and fire growth.
The FAA determined, in five incidents in the 1990s, that unexpected
flame spread along thermal and acoustic insulation-film covering
material, raising concerns about the fire performance of this material.
In all cases, the ignition source was relatively modest and, in most
cases, was electrical in origin (e.g., electrical short circuit, arcing
caused by chafed wiring, ruptured ballast case, etc.).
In 1996, the FAA Technical Center began a program to develop new
fire-test criteria for insulation films directly relating to in-flight
fire resistance. This development program resulted in a new test
method--the radiant-panel test--and also resulted in test criteria
specifically established for improving the in-flight fire ignition and
flame propagation of thermal and acoustic insulation materials based on
actual, on-board fire scenarios.
The FAA determined that a test similar to the test for the
measurement of insulation burnthrough resistance (14 CFR part 25,
Appendix F, Part VII, ``Test Method to Determine the Burnthrough
Resistance of Thermal/Acoustic Insulation Materials'') could be used to
assess the flammability characteristics of the proposed fuselage
aluminum-lithium material. The only change to the test is the size of
the sample and the sample holder, to accommodate panels of the fuselage
material.
Bombardier must use the test method contained in Part VII of
Appendix F, Test Method, for determining the burnthrough resistance of
thermal-acoustic insulation materials, with the slight changes to the
sample size and sample holder, as described in these special
conditions, to show that the aluminum-lithium material complies with
applicable requirements.
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.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-16-06-SC for the
Bombardier Model BD-700-2A12 and BD-700-2A11 airplanes was published in
the Federal Register on October 26, 2016 (81 FR 74348). One comment was
received.
The commenter acknowledged that the use of the aluminum-lithium
alloy would require full certification to the existing regulations.
However, they contend that the material is not novel and unusual and
does not require special conditions.
The FAA does not agree. While it is true that, with materials
presently tested, the proposed aluminum-lithium alloy does not appear
to pose a significant risk, the existing regulations and guidance do
not adequately address the use of this specific alloy technology.
Therefore, special conditions are required until the regulations
are amended to provide sufficient
[[Page 17533]]
requirements for the application of this new alloy technology.
Applicability
As discussed above, these special conditions are applicable to
Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes. Should
Bombardier 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 the other model as
well.
Conclusion
This action affects only a certain novel or unusual design feature
on Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes. It is not a
rule of general applicability and affects only the applicant who
applied to FAA for approval of this feature on the airplane.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Special Conditions
0
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 Bombardier Model BD-700-2A12 and BD-
700-2A13 airplanes.
1. Bombardier must demonstrate that the aluminum-lithium material
has equal or better flammability-resistance characteristics than the
aluminum-alloy sheet material typically used as skin material on
similar airplanes.
2. The test set-up and methodology must be in accordance with the
tests described in 14 CFR part 25, Appendix F, Part VII, except for the
following.
a. Each test sample must consist of a flat test specimen. A set of
three samples of aluminum-lithium sheet material must be tested. The
size of each sample must be 16 inches wide by 24 inches long by 0.063
inch thick.
b. The test samples must be installed into a steel-sheet subframe
with outside dimensions of 18 inches by 32 inches. The subframe must
have a 14.5-inch by 22.5-inch opening cut into it. The tests samples
must be mounted onto the subframe using 0.250-20 UNC threaded bolts.
c. Test specimens must be conditioned at 70 [deg]F + 5 [deg]F, and
55% + 5% humidity, for at least 24 hours before testing.
3. The aluminum-lithium material must not ignite during any of the
tests.
Issued in Renton, Washington, on April 3, 2017.
Michael Kaszycki,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2017-07326 Filed 4-11-17; 8:45 am]
BILLING CODE 4910-13-P
