Special Conditions: Airbus Model A380-800 Airplane, Escape Systems Inflation Systems, 46100-46102 [05-15648]
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46100
Federal Register / Vol. 70, No. 152 / Tuesday, August 9, 2005 / Proposed Rules
part 36. In addition, the FAA must issue
a finding of regulatory adequacy
pursuant to section 611 of Public Law
93–574, the ‘‘Noise Control Act of
1972.’’
Special conditions, as defined in 14
CFR 11.19, are issued in accordance
with 14 CFR 11.38 and become part of
the type certification basis in
accordance with 14 CFR 21.17(a)(2),
Amendment 21–69, effective September
16, 1991.
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 features, the special conditions
would also apply to the other model
under the provisions of 14 CFR
21.101(a)(1), Amendment 21–69,
effective September 16, 1991.
Discussion of Novel or Unusual Design
Features
All of the escape systems on the
upper deck and one pair of the escape
systems on the main deck of this
airplane are installed in non-pressurized
compartments. These non-pressurized
compartments will be exposed to
extremely cold temperatures on every
flight.
When the certification testing was
conducted for previous airplane
programs, the FAA considered that the
extreme environmental conditions to
which the escape systems can be
exposed would be independent of other
certification criteria. For example, the
escape system would be tested under
conditions of extreme cold in one test
and exposed to 25-knot winds at
ambient temperature in a separate test.
On the Model A380–800 airplane,
however, all the upper deck escape
systems and one pair of the main deck
escape systems are located in nonpressurized compartments. As a result,
these escape systems will be exposed to
extremely cold temperatures on every
flight. Therefore, the escape systems
must be tested under conditions of both
extremely cold temperatures and strong
winds.
In the past, several airplanes have had
a pair of escape systems installed in
non-pressurized compartments. These
escape systems were off-wing systems
that are less affected by wind than are
other escape systems, and only one pair
of exits was affected. Testing the
combined effects of extremely cold
temperature and strong winds was not
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15:10 Aug 08, 2005
Jkt 205001
required for these systems. On the A380,
however, one-half of the escape systems
are installed in non-pressurized
compartments. Therefore, the adverse
effects of a failure of the escape
system—due to the combination of
extremely cold temperatures and strong
wind—would be much more severe.
The regulations do not adequately
address escape systems installed in nonpressurized compartments; therefore,
the FAA is proposing a special
condition to require the applicant to
demonstrate that escape systems in nonpressurized compartments function
properly when exposed to both
extremely cold temperatures and strong
winds.
Applicability
As discussed above, these special
conditions are applicable to the Airbus
A380–800 airplane. Should Airbus
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design features, these special
conditions would apply to that model as
well under the provisions of
§ 21.101(a)(1), Amendment 21–69,
effective September 16, 1991.
Conclusion
This action affects only certain novel
or unusual design features of the Airbus
A380–800 airplane. It is not a rule of
general applicability, and it affects only
the applicant which applied to the FAA
for approval of these features 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:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for the
Airbus A380–800 airplane.
In addition to the requirements of
§§ 25.810, 25.1301 and 25.1309, the
following special condition applies:
For the escape systems on the Model
A380 airplane that are installed in nonpressurized compartments and thus are
exposed to extremely cold temperatures
on every flight, it must be demonstrated
that the escape systems function
properly in the combination of the cold
soak associated with long flight at
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
altitude and a 25-knot wind from the
critical angle.
Issued in Renton, Washington, on July 19,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–15647 Filed 8–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM320; Notice No. 25–05–15–
SC]
Special Conditions: Airbus Model
A380–800 Airplane, Escape Systems
Inflation Systems
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
SUMMARY: This notice proposes special
conditions for the Airbus A380–800
airplane. This airplane will have novel
or unusual design features when
compared to the state of technology
envisioned in the airworthiness
standards for transport category
airplanes. Many of these novel or
unusual design features are associated
with the complex systems and the
configuration of the airplane, including
its full-length double deck. For these
design features, the applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
regarding escape system reliability.
These proposed 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.
Additional special conditions will be
issued for other novel or unusual design
features of the Airbus Model A380–800
airplane.
DATES: Comments must be received on
or before September 23, 2005.
ADDRESSES: Comments on this proposal
may be mailed in duplicate to: Federal
Aviation Administration, Transport
Airplane Directorate, Attention: Rules
Docket (ANM–113), Docket No. NM320,
1601 Lind Avenue SW., Renton,
Washington 98055–4056; or delivered in
duplicate to the Transport Airplane
Directorate at the above address. All
comments must be marked: Docket
No.NM 320. Comments may be
inspected in the Rules Docket
E:\FR\FM\09AUP1.SGM
09AUP1
Federal Register / Vol. 70, No. 152 / Tuesday, August 9, 2005 / Proposed Rules
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT:
Holly Thorson, FAA, International
Branch, ANM–116, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW.,
Renton, Washington 98055–4056;
telephone (425) 227–1357; facsimile
(425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites interested persons to
participate in this rulemaking by
submitting 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 ask that
you send us two copies of written
comments.
We will file in the docket all
comments we receive as well as a report
summarizing each substantive public
contact with FAA personnel concerning
these proposed special conditions. The
docket is available for public inspection
before and after the comment closing
date. If you wish to review the docket
in person, go to the address in the
ADDRESSES section of this notice
between 7:30 a.m. and 4 p.m., Monday
through Friday, except Federal holidays.
We will consider all comments we
receive on or before the closing date for
comments. We will consider comments
filed late, if it is possible to do so
without incurring expense or delay. We
may change the proposed special
conditions in light of the comments we
receive.
If you want the FAA to acknowledge
receipt of your comments on this
proposal, include with your comments
a pre-addressed, stamped postcard on
which the docket number appears. We
will stamp the date on the postcard and
mail it back to you.
Background
Airbus applied for FAA certification/
validation of the provisionallydesignated Model A3XX–100 in its
letter AI/L 810.0223/98, dated August
12, 1998, to the FAA. Application for
certification by the Joint Aviation
Authorities (JAA) of Europe had been
made on January 16, 1998, reference AI/
L 810.0019/98. In its letter to the FAA,
Airbus requested an extension to the 5year period for type certification in
accordance with 14 CFR 21.17(c). The
request was for an extension to a 7-year
period, using the date of the initial
application letter to the JAA as the
reference date. The reason given by
VerDate jul<14>2003
15:10 Aug 08, 2005
Jkt 205001
Airbus for the request for extension is
related to the technical challenges,
complexity, and the number of new and
novel features on the airplane. On
November 12, 1998, the Manager,
Aircraft Engineering Division, AIR–100,
granted Airbus’ request for the 7-year
period, based on the date of application
to the JAA.
In its letter AI/LE–A 828.0040/99
Issue 3, dated July 20, 2001, Airbus
stated that its target date for type
certification of the Model A380–800 has
been moved from May 2005, to January
2006, to match the delivery date of the
first production airplane. In accordance
with 14 CFR 21.17(d)(2), Airbus chose a
new application date of April 20, 1999,
and requested that the 7-year
certification period which had already
been approved be continued. The part
25 certification basis for the Model
A380–800 airplane was adjusted to
reflect the new application date.
The Model A380–800 airplane will be
an all-new, four-engine jet transport
airplane with a full double-deck, twoaisle cabin. The maximum takeoff
weight will be 1.235 million pounds
with a typical three-class layout of 555
passengers.
Type Certification Basis
Under the provisions of 14 CFR 21.17,
Airbus must show that the Model A380–
800 airplane meets the applicable
provisions of 14 CFR part 25, as
amended by Amendments 25–1 through
25–98. If the Administrator finds that
the applicable airworthiness regulations
do not contain adequate or appropriate
safety standards for the Airbus A380–
800 airplane because of novel or
unusual design features, special
conditions are prescribed under the
provisions of 14 CFR 21.16.
In addition to the applicable
airworthiness regulations and special
conditions, the Airbus Model A380–800
airplane 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. In addition, the FAA must issue
a finding of regulatory adequacy
pursuant to section 611 of Public Law
93–574, the ‘‘Noise Control Act of
1972.’’
Special conditions, as defined in 14
CFR 11.19, are issued in accordance
with 14 CFR 11.38 and become part of
the type certification basis in
accordance with 14 CFR 21.17(a)(2),
Amendment 21–69, effective September
16, 1991.
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
46101
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 features, the special conditions
would also apply to the other model
under the provisions of 14 CFR
21.101(a)(1), Amendment 21–69,
effective September 16, 1991.
Discussion of Novel or Unusual Design
Features
The inflation system for the escape
systems associated with the exits
includes a pressurized cylinder with a
mixture of carbon dioxide and argon in
both gaseous and liquid states. The
inflation system also includes a smaller
cylinder containing a solid propellant
that burns to generate gaseous
propellant. The opening of the valve
and the ignition of the propellant are
accomplished by the firing of squibs.
The firing of these squibs is sequenced
to improve their performance in the
extreme temperatures to which they are
subjected. Firing of the squibs is
controlled by a system mounted on the
the emergency exit.
The proposed design for the escape
systems on the A380 is much more
complex than the design of systems
currently in use. Typically, inflation
systems for escape systems consist of a
pressurized cylinder containing a
mixture of gases and a regulator valve
that reduces the outlet pressure
supplied from the inflation cylinder.
The regulator valve is opened either by
mechanical means or by the firing of a
squib.
The regulations governing the
certification of the A380 do not
adequately address the certification
requirements of this type of inflation
system for an escape system.
Furthermore, the Technical Standard
Order (TSO) that addresses escape
systems (i.e., TSO–C69c) does not
adequately address this type of inflation
system. The current requirements for
escape system reliability are predicated
on a simple inflation system, where
reliability is driven by the performance
of the inflatable itself. The existing
requirements do not account for an
inflation system that could adversely
affect the overall reliability of the escape
system.
Since the A380 has 16 emergency
exits, the requirements of § 25.810
require a total of 80 successful
deployments (5 successive deployments
for each exit). However, since the
requirements apply to each system
independently, failures in a system
common to all the escape systems
E:\FR\FM\09AUP1.SGM
09AUP1
46102
Federal Register / Vol. 70, No. 152 / Tuesday, August 9, 2005 / Proposed Rules
would not be adequately addressed.
Therefore, the inflation system needs a
specific requirement that will show
adequate system reliability. With a goal
of achieving 95% reliability of the
inflation system with a 95% confidence,
we are establishing such a requirement.
As we noted above, the propellant used
is designed to burn. The regulations do
not address this type of propellant, and
some measure of fire safety protection is
needed. United Nations document
No.ST/SG/AC.10/I1/Rev.3 ‘‘Transport of
Dangerous Goods, Manual of Tests and
Criteria,’’ section 13.7.1 contains a small
scale test that addresses this concern.
Propellants that pass this test will not be
a fire hazard.
Therefore, the FAA is proposing a
special condition to ensure that the
inflation system for the A380 escape
system is reliable and that the
propellant itself does not constitute a
fire hazard.
Applicability
As discussed above, these special
conditions are applicable to the Airbus
A380–800 airplane. Should Airbus
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design features, these special
conditions would apply to that model as
well under the provisions of
§ 21.101(a)(1), Amendment 21–69,
effective September 16, 1991.
Conclusion
This action affects only certain novel
or unusual design features of the Airbus
A380–800 airplane. It is not a rule of
general applicability, and it affects only
the applicant which applied to the FAA
for approval of these features 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:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for the
Airbus A380–800 airplane.
a. In addition to the requirements of
§ 25.810, the following special
conditions apply:
To ensure that the inflation system is
a reliable design, it must be tested using
84 inflation/firing system bench tests
VerDate jul<14>2003
15:10 Aug 08, 2005
Jkt 205001
with no more than one failure. For these
special conditions, the inflation/firing
system is defined as everything
upstream of the outlet connection to the
inflation valve, which includes but is
not limited to the door-mounted
systems that provide the firing signals to
the squibs, the squibs themselves, the
solid propellant, and the valve.
b. In addition to the requirements of
§ 25.853(a) and Appendix F Part I (a)(ii),
in standard atmosphere conditions the
following special conditions apply:
To ensure that the propellant itself
does not contribute significantly to a
fire, the propellant must be subjected to
and must pass a standard ‘‘Small-Scale
Burning Test,’’ as specified in United
Nations document No.ST/SG/AC.10/I1/
Rev.3 ‘‘Transport of Dangerous Goods,
Manual of Tests and Criteria,’’ section
13.7.1.
Issued in Renton, Washington, on July 25,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–15648 Filed 8–8–05; 8:45 am]
BILLING CODE 4910–13–P
special conditions will be issued for
other novel or unusual design features
of the Airbus Model A380–800 airplane.
DATES: Comments must be received on
or before September 23, 2005.
ADDRESSES: Comments on this proposal
may be mailed in duplicate to: Federal
Aviation Administration, Transport
Airplane Directorate, Attention: Rules
Docket (ANM–113), Docket No. NM319,
1601 Lind Avenue SW., Renton,
Washington 98055–4056; or delivered in
duplicate to the Transport Airplane
Directorate at the above address. All
comments must be marked: Docket No.
NM319. Comments may be inspected in
the Rules Docket weekdays, except
Federal holidays, between 7:30 a.m. and
4 p.m.
FOR FURTHER INFORMATION CONTACT:
Holly Thorson, FAA, International
Branch, ANM–116, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW.,
Renton, Washington 98055–4056;
telephone (425) 227–1357; facsimile
(425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM319; Notice No. 25–05–14–
SC]
Special Conditions: Airbus Model
A380–800 Airplane, Crashworthiness
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
SUMMARY: This notice proposes special
conditions for the Airbus A380–800
airplane. This airplane will have novel
or unusual design features when
compared to the state of technology
envisioned in the airworthiness
standards for transport category
airplanes. Many of these novel or
unusual design features are associated
with the complex systems and the
configuration of the airplane, including
its full-length double deck. For these
design features, the applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
regarding crash survivability. These
proposed 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. Additional
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
The FAA invites interested persons to
participate in this rulemaking by
submitting 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 ask that
you send us two copies of written
comments.
We will file in the docket all
comments we receive as well as a report
summarizing each substantive public
contact with FAA personnel concerning
these proposed special conditions. The
docket is available for public inspection
before and after the comment closing
date. If you wish to review the docket
in person, go to the address in the
ADDRESSES section of this notice
between 7:30 a.m. and 4 p.m., Monday
through Friday, except Federal holidays.
We will consider all comments we
receive on or before the closing date for
comments. We will consider comments
filed late, if it is possible to do so
without incurring expense or delay. We
may change the proposed special
conditions in light of the comments we
receive.
If you want the FAA to acknowledge
receipt of your comments on this
proposal, include with your comments
a pre-addressed, stamped postcard on
which the docket number appears. We
will stamp the date on the postcard and
mail it back to you.
E:\FR\FM\09AUP1.SGM
09AUP1
]]>Agencies
[Federal Register Volume 70, Number 152 (Tuesday, August 9, 2005)]
[Proposed Rules]
[Pages 46100-46102]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-15648]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM320; Notice No. 25-05-15-SC]
Special Conditions: Airbus Model A380-800 Airplane, Escape
Systems Inflation Systems
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
-----------------------------------------------------------------------
SUMMARY: This notice proposes special conditions for the Airbus A380-
800 airplane. This airplane will have novel or unusual design features
when compared to the state of technology envisioned in the
airworthiness standards for transport category airplanes. Many of these
novel or unusual design features are associated with the complex
systems and the configuration of the airplane, including its full-
length double deck. For these design features, the applicable
airworthiness regulations do not contain adequate or appropriate safety
standards regarding escape system reliability. These proposed 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.
Additional special conditions will be issued for other novel or unusual
design features of the Airbus Model A380-800 airplane.
DATES: Comments must be received on or before September 23, 2005.
ADDRESSES: Comments on this proposal may be mailed in duplicate to:
Federal Aviation Administration, Transport Airplane Directorate,
Attention: Rules Docket (ANM-113), Docket No. NM320, 1601 Lind Avenue
SW., Renton, Washington 98055-4056; or delivered in duplicate to the
Transport Airplane Directorate at the above address. All comments must
be marked: Docket No.NM 320. Comments may be inspected in the Rules
Docket
[[Page 46101]]
weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Holly Thorson, FAA, International
Branch, ANM-116, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone
(425) 227-1357; facsimile (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites interested persons to participate in this
rulemaking by submitting 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 ask that you send us two copies of written
comments.
We will file in the docket all comments we receive as well as a
report summarizing each substantive public contact with FAA personnel
concerning these proposed special conditions. The docket is available
for public inspection before and after the comment closing date. If you
wish to review the docket in person, go to the address in the ADDRESSES
section of this notice between 7:30 a.m. and 4 p.m., Monday through
Friday, except Federal holidays.
We will consider all comments we receive on or before the closing
date for comments. We will consider comments filed late, if it is
possible to do so without incurring expense or delay. We may change the
proposed special conditions in light of the comments we receive.
If you want the FAA to acknowledge receipt of your comments on this
proposal, include with your comments a pre-addressed, stamped postcard
on which the docket number appears. We will stamp the date on the
postcard and mail it back to you.
Background
Airbus applied for FAA certification/validation of the
provisionally-designated Model A3XX-100 in its letter AI/L 810.0223/98,
dated August 12, 1998, to the FAA. Application for certification by the
Joint Aviation Authorities (JAA) of Europe had been made on January 16,
1998, reference AI/L 810.0019/98. In its letter to the FAA, Airbus
requested an extension to the 5-year period for type certification in
accordance with 14 CFR 21.17(c). The request was for an extension to a
7-year period, using the date of the initial application letter to the
JAA as the reference date. The reason given by Airbus for the request
for extension is related to the technical challenges, complexity, and
the number of new and novel features on the airplane. On November 12,
1998, the Manager, Aircraft Engineering Division, AIR-100, granted
Airbus' request for the 7-year period, based on the date of application
to the JAA.
In its letter AI/LE-A 828.0040/99 Issue 3, dated July 20, 2001,
Airbus stated that its target date for type certification of the Model
A380-800 has been moved from May 2005, to January 2006, to match the
delivery date of the first production airplane. In accordance with 14
CFR 21.17(d)(2), Airbus chose a new application date of April 20, 1999,
and requested that the 7-year certification period which had already
been approved be continued. The part 25 certification basis for the
Model A380-800 airplane was adjusted to reflect the new application
date.
The Model A380-800 airplane will be an all-new, four-engine jet
transport airplane with a full double-deck, two-aisle cabin. The
maximum takeoff weight will be 1.235 million pounds with a typical
three-class layout of 555 passengers.
Type Certification Basis
Under the provisions of 14 CFR 21.17, Airbus must show that the
Model A380-800 airplane meets the applicable provisions of 14 CFR part
25, as amended by Amendments 25-1 through 25-98. If the Administrator
finds that the applicable airworthiness regulations do not contain
adequate or appropriate safety standards for the Airbus A380-800
airplane because of novel or unusual design features, special
conditions are prescribed under the provisions of 14 CFR 21.16.
In addition to the applicable airworthiness regulations and special
conditions, the Airbus Model A380-800 airplane 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. In addition, the
FAA must issue a finding of regulatory adequacy pursuant to section 611
of Public Law 93-574, the ``Noise Control Act of 1972.''
Special conditions, as defined in 14 CFR 11.19, are issued in
accordance with 14 CFR 11.38 and become part of the type certification
basis in accordance with 14 CFR 21.17(a)(2), Amendment 21-69, effective
September 16, 1991.
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 features, the special conditions would also apply to the
other model under the provisions of 14 CFR 21.101(a)(1), Amendment 21-
69, effective September 16, 1991.
Discussion of Novel or Unusual Design Features
The inflation system for the escape systems associated with the
exits includes a pressurized cylinder with a mixture of carbon dioxide
and argon in both gaseous and liquid states. The inflation system also
includes a smaller cylinder containing a solid propellant that burns to
generate gaseous propellant. The opening of the valve and the ignition
of the propellant are accomplished by the firing of squibs. The firing
of these squibs is sequenced to improve their performance in the
extreme temperatures to which they are subjected. Firing of the squibs
is controlled by a system mounted on the the emergency exit.
The proposed design for the escape systems on the A380 is much more
complex than the design of systems currently in use. Typically,
inflation systems for escape systems consist of a pressurized cylinder
containing a mixture of gases and a regulator valve that reduces the
outlet pressure supplied from the inflation cylinder. The regulator
valve is opened either by mechanical means or by the firing of a squib.
The regulations governing the certification of the A380 do not
adequately address the certification requirements of this type of
inflation system for an escape system. Furthermore, the Technical
Standard Order (TSO) that addresses escape systems (i.e., TSO-C69c)
does not adequately address this type of inflation system. The current
requirements for escape system reliability are predicated on a simple
inflation system, where reliability is driven by the performance of the
inflatable itself. The existing requirements do not account for an
inflation system that could adversely affect the overall reliability of
the escape system.
Since the A380 has 16 emergency exits, the requirements of Sec.
25.810 require a total of 80 successful deployments (5 successive
deployments for each exit). However, since the requirements apply to
each system independently, failures in a system common to all the
escape systems
[[Page 46102]]
would not be adequately addressed. Therefore, the inflation system
needs a specific requirement that will show adequate system
reliability. With a goal of achieving 95% reliability of the inflation
system with a 95% confidence, we are establishing such a requirement.
As we noted above, the propellant used is designed to burn. The
regulations do not address this type of propellant, and some measure of
fire safety protection is needed. United Nations document No.ST/SG/
AC.10/I1/Rev.3 ``Transport of Dangerous Goods, Manual of Tests and
Criteria,'' section 13.7.1 contains a small scale test that addresses
this concern. Propellants that pass this test will not be a fire
hazard.
Therefore, the FAA is proposing a special condition to ensure that
the inflation system for the A380 escape system is reliable and that
the propellant itself does not constitute a fire hazard.
Applicability
As discussed above, these special conditions are applicable to the
Airbus A380-800 airplane. Should Airbus apply at a later date for a
change to the type certificate to include another model incorporating
the same novel or unusual design features, these special conditions
would apply to that model as well under the provisions of Sec.
21.101(a)(1), Amendment 21-69, effective September 16, 1991.
Conclusion
This action affects only certain novel or unusual design features
of the Airbus A380-800 airplane. It is not a rule of general
applicability, and it affects only the applicant which applied to the
FAA for approval of these features 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:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Proposed Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration (FAA) proposes the
following special conditions as part of the type certification basis
for the Airbus A380-800 airplane.
a. In addition to the requirements of Sec. 25.810, the following
special conditions apply:
To ensure that the inflation system is a reliable design, it must
be tested using 84 inflation/firing system bench tests with no more
than one failure. For these special conditions, the inflation/firing
system is defined as everything upstream of the outlet connection to
the inflation valve, which includes but is not limited to the door-
mounted systems that provide the firing signals to the squibs, the
squibs themselves, the solid propellant, and the valve.
b. In addition to the requirements of Sec. 25.853(a) and Appendix
F Part I (a)(ii), in standard atmosphere conditions the following
special conditions apply:
To ensure that the propellant itself does not contribute
significantly to a fire, the propellant must be subjected to and must
pass a standard ``Small-Scale Burning Test,'' as specified in United
Nations document No.ST/SG/AC.10/I1/Rev.3 ``Transport of Dangerous
Goods, Manual of Tests and Criteria,'' section 13.7.1.
Issued in Renton, Washington, on July 25, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-15648 Filed 8-8-05; 8:45 am]
BILLING CODE 4910-13-P
