Special Conditions: Airbus Model A380-800 Airplane, Escape Systems Installed in Non-Pressurized Compartments, 53313-53315 [E6-15011]
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Federal Register / Vol. 71, No. 175 / Monday, September 11, 2006 / Rules and Regulations
suggests replacing the word ‘‘control’’
with the word ‘‘manage’’ [or
‘‘management’’] to reflect a more
realistic situation.
FAA response: The direct view
requirements will be applied to the
stairs as they are to other egress paths.
The FAA agrees that ‘‘manage’’ is a
better term than ‘‘control’’ and has
changed the text of Special Condition d.
accordingly.
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.
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.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
I The authority citation for these
special conditions is as follows:
bjneal on PROD1PC71 with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
I 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 the Airbus A380–800 airplane.
In addition to the requirements of
§§ 25.803 and 25.811 through 25.813,
the following special conditions apply:
a. At least one stairway between decks
must meet the following requirements:
The stairway accommodates the
carriage of an incapacitated person from
one deck to the other. The crew member
procedures for such carriage must be
established.
b. There must be at least two
stairways between decks that meet the
following requirements: The stairways
must be designed such that evacuees
can achieve an adequate rate for going
down or going up under probable
emergency conditions, including a
condition in which a person falls or is
incapacitated while on a stairway. One
of the stairways must be the stairway
specified in paragraph a. above.
c. Each stairway between decks must
meet the following requirements:
1. It must have an entrance, exit, and
gradient characteristics that—with the
assistance of a crew member—would
VerDate Aug<31>2005
16:10 Sep 08, 2006
Jkt 208001
allow the passengers of one deck to
merge with passengers of the other deck
during an evacuation and exit the
airplane. These entrance, exit, and
gradient characteristics must occur with
the airplane in level attitude and in each
attitude resulting from the collapse of
any one or more legs of the landing gear.
These requirements must be
demonstrated by tests and/or analysis.
2. The stairway must have a handrail
on at least one side in order to allow
people to steady themselves during
foreseeable conditions, including but
not limited to the condition of gear
collapse on the ground and moderate
turbulence in flight. The handrails must
be constructed, so that there will be no
obstruction on them which will cause
the user to release his/her grip on the
handrail or will hinder the continuous
movement of the hands along the
handrail. Handrails must be terminated
in a manner which will not obstruct
pedestrian travel or create a hazard.
Adequacy of the design must be
demonstrated by using persons
representative of the 5% female and the
95% male.
3. The stairway must be designed and
located to minimize damage to it during
an emergency landing or ditching.
4. The stairway must have a wall or
the equivalent on each side to minimize
the risk of falling and to facilitate use of
the stairway under conditions of
abnormal airplane attitude.
5. Treads and landings must be
designed and demonstrated to be free of
hazard. The landing area at each deck
level must be demonstrated to be
adequate in terms of flow rate for the
maximum number of people that will be
using the stair in an emergency. Treads
and risers must be designed to ensure an
easy and safe use of the stairway.
6. General emergency illumination
must be provided so that—when
measured along the centerlines of each
tread and landing—the illumination is
not less than 0.05 foot-candle.
7. In normal operation, the general
illumination level must not be less than
0.05 foot-candles. The assessment must
be done under day light and dark of
night conditions.
8. Both stairway ends must be
indicated by an exit sign visible to
passengers when in the stairway. This
exit sign must meet the requirements of
§ 25.812(b)(1)(ii).
9. A floor proximity path marking
system which meets the requirements of
§ 25.812(e) must be available to guide
passengers in the stairway to the
stairway ends. It must not direct the
occupants of the cabin to the stair
entrance.
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Frm 00015
Fmt 4700
Sfmt 4700
53313
10. The public address system must
be audible in the stairway during all
flight phases.
11. ‘‘No smoking’’ and ‘‘return to
seat’’ signs must be installed and must
be visible in the stairway both going up
and down and at the stairway entrances.
d. Cabin crew procedures and
positions must be established to manage
the use of the stairs on the ground and
in flight under both normal and
emergency situations. This may require
that cabin crew members have specific
dedicated duties for the management of
the stairs during emergency and
precautionary evacuations.
e. It should not be hazardous for crew
members or passengers who are
returning to their seats to use the
stairways during moderate turbulence.
Issued in Renton, Washington, on August
28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–15001 Filed 9–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM318; Special Conditions No.
25–329–SC]
Special Conditions: Airbus Model
A380–800 Airplane, Escape Systems
Installed in Non-Pressurized
Compartments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
SUMMARY: These special conditions are
issued 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 systems installed in
non-pressurized compartments. 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. Additional
E:\FR\FM\11SER1.SGM
11SER1
53314
Federal Register / Vol. 71, No. 175 / Monday, September 11, 2006 / Rules and Regulations
special conditions will be issued for
other novel or unusual design features
of the Airbus Model A380–800 airplane.
DATES: Effective Date: The effective date
of these special conditions is August 28,
2006.
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:
bjneal on PROD1PC71 with RULES
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
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 had
been moved from May 2005, to January
2006, to match the delivery date of the
first production airplane. In a
subsequent letter (AI/L 810.0223/98
issue 3, dated January 27, 2006), Airbus
stated that its target date for type
certification is October 2, 2006. In
accordance with 14 CFR 21.17(d)(2),
Airbus chose a new application date of
December 20, 1999, and requested that
the 7-year certification period which
had already been approved be
continued. The FAA has reviewed the
part 25 certification basis for the Model
A380–800 airplane, and no changes are
required based on 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
VerDate Aug<31>2005
16:10 Sep 08, 2006
Jkt 208001
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).
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, the special conditions
would also apply to the other model
under the provisions of 14 CFR 21.101.
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 one
another. 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
non-pressurized compartments. As a
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
result, these escape systems will be
exposed to extremely cold temperatures
on every flight. Therefore, they 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
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, a
special condition is needed to require
the applicant to demonstrate that escape
systems in non-pressurized
compartments function properly when
exposed to both extremely cold
temperatures and strong winds.
Discussion of Comments
Notice of Proposed Special
Conditions No. 25–05–13–SC,
pertaining to escape systems installed in
non-pressurized compartments, was
published in the Federal Register on
August 9, 2005 (70 FR 46099).
Comments were received from the
Airline Pilots Association (ALPA) and
from an individual commenter.
Requested change 1: ALPA suggests
that the special conditions ‘‘should be
amended to ensure that the testing done
to evaluate that the escape system
functions correctly after exposure to
cold soak and high altitude also
evaluates the repeated cycling of these
parameters. In addition, exposure to
heat and humidity, water intrusion and
the introduction of precipitation
propelled at and past the slide
compartment at speeds equal to those
used in approaches and departures
should also be evaluated.’’
FAA response: Evaluation of the
response of the escape systems installed
in non-pressurized compartments to
these environmental conditions is
required by 14 CFR 25.1309 and will be
addressed as part as the compliance
demonstration for the escape systems.
Accordingly, we have not changed the
special condition, as proposed.
Requested change 2: The individual
commenter addresses the stowage of
survival kits with the slide/rafts in non-
E:\FR\FM\11SER1.SGM
11SER1
Federal Register / Vol. 71, No. 175 / Monday, September 11, 2006 / Rules and Regulations
pressurized locations. He states that,
‘‘The safety issue is that the life/raft
items are not immediately ready and
attached to the slide/raft in a ditching as
they are on slide/rafts stored in the
pressurized section of aircraft.’’
FAA response: Stowage of survival
kits has not yet been resolved for the
upper deck slide/rafts. In the case of
portable life rafts, the entire raft must be
retrieved for ditching; with slide/rafts,
the raft is available automatically when
the exit is opened. It may be feasible to
stow the survival kit separately from the
slide/raft and maintain the same level of
safety as that provided by portable rafts,
and that would be an acceptable design
alternative. This can be addressed
within the existing regulations.
Therefore, no change has been made to
the special conditions, as proposed.
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.
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.
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:
I
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 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
A380–800 airplane that are installed in
non-pressurized 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 altitude and a 25-knot wind from the
critical angle.
bjneal on PROD1PC71 with RULES
I
VerDate Aug<31>2005
16:10 Sep 08, 2006
Jkt 208001
Issued in Renton, Washington, on August
28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–15011 Filed 9–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM317; Special Conditions No.
25–328–SC]
Special Conditions: Airbus Model
A380–800 Airplane, Flotation and
Ditching
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
SUMMARY: These special conditions are
issued 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 flotation and ditching. 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: Effective Date: The effective date
of these special conditions is August 28,
2006.
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:
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
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
53315
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
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 had
been moved from May 2005, to January
2006, to match the delivery date of the
first production airplane. In a
subsequent letter (AI/L 810.0223/98
issue 3, dated January 27, 2006), Airbus
stated that its target date for type
certification is October 2, 2006. In
accordance with 14 CFR 21.17(d)(2),
Airbus chose a new application date of
December 20, 1999, and requested that
the 7-year certification period which
had already been approved be
continued. The FAA has reviewed the
part 25 certification basis for the Model
A380–800 airplane, and no changes are
required based on 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
E:\FR\FM\11SER1.SGM
11SER1
]]>Agencies
[Federal Register Volume 71, Number 175 (Monday, September 11, 2006)]
[Rules and Regulations]
[Pages 53313-53315]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-15011]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM318; Special Conditions No. 25-329-SC]
Special Conditions: Airbus Model A380-800 Airplane, Escape
Systems Installed in Non-Pressurized Compartments
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued 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
systems installed in non-pressurized compartments. 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.
Additional
[[Page 53314]]
special conditions will be issued for other novel or unusual design
features of the Airbus Model A380-800 airplane.
DATES: Effective Date: The effective date of these special conditions
is August 28, 2006.
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:
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 had been moved from May 2005, to January 2006, to match the
delivery date of the first production airplane. In a subsequent letter
(AI/L 810.0223/98 issue 3, dated January 27, 2006), Airbus stated that
its target date for type certification is October 2, 2006. In
accordance with 14 CFR 21.17(d)(2), Airbus chose a new application date
of December 20, 1999, and requested that the 7-year certification
period which had already been approved be continued. The FAA has
reviewed the part 25 certification basis for the Model A380-800
airplane, and no changes are required based on 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).
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, the special conditions would also apply to the
other model under the provisions of 14 CFR 21.101.
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 one
another. 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 non-pressurized compartments. As a
result, these escape systems will be exposed to extremely cold
temperatures on every flight. Therefore, they 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 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 non-pressurized compartments; therefore, a special condition is
needed to require the applicant to demonstrate that escape systems in
non-pressurized compartments function properly when exposed to both
extremely cold temperatures and strong winds.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-05-13-SC, pertaining
to escape systems installed in non-pressurized compartments, was
published in the Federal Register on August 9, 2005 (70 FR 46099).
Comments were received from the Airline Pilots Association (ALPA) and
from an individual commenter.
Requested change 1: ALPA suggests that the special conditions
``should be amended to ensure that the testing done to evaluate that
the escape system functions correctly after exposure to cold soak and
high altitude also evaluates the repeated cycling of these parameters.
In addition, exposure to heat and humidity, water intrusion and the
introduction of precipitation propelled at and past the slide
compartment at speeds equal to those used in approaches and departures
should also be evaluated.''
FAA response: Evaluation of the response of the escape systems
installed in non-pressurized compartments to these environmental
conditions is required by 14 CFR 25.1309 and will be addressed as part
as the compliance demonstration for the escape systems. Accordingly, we
have not changed the special condition, as proposed.
Requested change 2: The individual commenter addresses the stowage
of survival kits with the slide/rafts in non-
[[Page 53315]]
pressurized locations. He states that, ``The safety issue is that the
life/raft items are not immediately ready and attached to the slide/
raft in a ditching as they are on slide/rafts stored in the pressurized
section of aircraft.''
FAA response: Stowage of survival kits has not yet been resolved
for the upper deck slide/rafts. In the case of portable life rafts, the
entire raft must be retrieved for ditching; with slide/rafts, the raft
is available automatically when the exit is opened. It may be feasible
to stow the survival kit separately from the slide/raft and maintain
the same level of safety as that provided by portable rafts, and that
would be an acceptable design alternative. This can be addressed within
the existing regulations. Therefore, no change has been made to the
special conditions, as proposed.
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.
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.
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 the Airbus A380-800 airplane.
In addition to the requirements of Sec. Sec. 25.810, 25.1301 and
25.1309, the following special condition applies:
For the escape systems on the Model A380-800 airplane that are
installed in non-pressurized 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 altitude and a 25-knot wind
from the critical angle.
Issued in Renton, Washington, on August 28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-15011 Filed 9-8-06; 8:45 am]
BILLING CODE 4910-13-P
