Special Conditions: Airbus Model A380-800 Airplane, Design Roll Maneuver, 38513-38515 [E6-10673]
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38513
Rules and Regulations
Federal Register
Vol. 71, No. 130
Friday, July 7, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
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are keyed to and codified in the Code of
Federal Regulations, which is published under
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The Code of Federal Regulations is sold by
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REGISTER issue of each week.
FEDERAL ELECTION COMMISSION
11 CFR Part 104
[Notice 2006–11]
Statement of Policy; Recordkeeping
Requirements for Payroll Deduction
Authorizations
Federal Election Commission.
Statement of policy.
AGENCY:
cprice-sewell on PROD1PC66 with RULES
ACTION:
SUMMARY: The Commission has
previously sought copies of original
signed payroll deduction authorization
forms as the sole adequate proof that
contributors intended to authorize
payroll deduction to make contributions
to the separate segregated fund of a
corporation, labor organization, or trade
association. As a matter of general
policy, the Commission intends to
accept certain other forms of
documentation as proof of payroll
deduction authorization, which are
described in the supplementary
information below.
DATES: Effective Date: July 7, 2006.
FOR FURTHER INFORMATION CONTACT: Mr.
Richard T. Ewell, Attorney, 999 E Street,
NW., Washington, DC 20463, (202) 694–
1650 or (800) 424–9530.
SUPPLEMENTARY INFORMATION:
Corporations, labor organizations, and
trade associations may use a payroll
deduction system to collect and forward
voluntary contributions from certain
persons to their separate segregated
funds (‘‘SSFs’’), which are political
committees they establish. 11 CFR
114.2(f)(4)(i). Political committees must
maintain records that provide sufficient
detail to enable the Commission to
verify that the source and amount of
contributions received by the committee
are accurately and completely reported.
See 11 CFR 104.14(b)(1); see also 11
CFR 104.8(b) (reporting contributions
received through payroll deductions).
For contributions collected by payroll
VerDate Aug<31>2005
15:33 Jul 06, 2006
Jkt 208001
deduction, the Commission’s past
practice had been to request copies of
original signed payroll deduction
authorization (‘‘PDA’’) forms as proof
that the SSF satisfied the recordkeeping
requirements of 11 CFR 104.14(b)(1).
Through this statement of policy, the
Commission announces that signed PDA
forms are not the only adequate form of
proof for meeting the recordkeeping
requirements of 11 CFR 104.14(b)(1).
As a matter of general policy, the
Commission intends to accept other
evidence that the requirements of 11
CFR 104.14 have been satisfied, which
may include records of the transmittal
of funds from employers or collecting
agents, including spreadsheets or other
computerized records, wire transfer
records, or other written or electronic
records.
SSFs are advised, however, that the
Commission considers the retention of
signed PDA forms to be a sound
recordkeeping practice, and in many
cases, signed PDA forms may serve as
the best documentation that a deduction
was authorized at a particular time for
a particular amount. Additionally, some
SSFs are subject to independent PDA
recordkeeping requirements under State
law. The Commission’s policy does not
alter or affect a committee’s
recordkeeping obligations under any
applicable State law.
This Federal Register notice
represents a general statement of policy
announcing the general course of action
that the Commission intends to follow.
This policy statement does not
constitute an agency regulation
requiring notice of proposed
rulemaking, opportunities for public
participation, prior publication, and
delay in effective date under 5 U.S.C.
553 of the Administrative Procedure Act
(‘‘APA’’). As such, it does not bind the
Commission or any member of the
general public. The provisions of the
Regulatory Flexibility Act, which apply
when notice and comment are required
by the APA or another statute, are not
applicable.
Dated: June 30, 2006.
Michael E. Toner,
Chairman, Federal Election Commission.
[FR Doc. E6–10629 Filed 7–6–06; 8:45 am]
BILLING CODE 6715–01–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM340; Special Conditions No.
25–318–SC]
Special Conditions: Airbus Model
A380–800 Airplane, Design Roll
Maneuver
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
for design roll maneuvers. 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 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 June 29,
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
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07JYR1
38514
Federal Register / Vol. 71, No. 130 / Friday, July 7, 2006 / Rules and Regulations
cprice-sewell on PROD1PC66 with RULES
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
certification requirements of 14 CFR
part 36. In addition, the FAA must issue
VerDate Aug<31>2005
15:33 Jul 06, 2006
Jkt 208001
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
The A380 is equipped with an
electronic flight control system. In this
system, there is not a direct mechanical
link between the airplane flight control
surface and the pilot’s cockpit control
device as there is on more conventional
airplanes. Instead, a flight control
computer commands the airplane flight
control surfaces, based on input
received from the cockpit control
device. The pilot input is modified by
the flight control computer—based on
the current airplane flight parameters
before the command is given to the
flight control surface. Therefore, there is
not a direct mechanical relationship
between the pilot command and the
command given to the control surface.
The formulation of airplane design
load conditions in 14 CFR part 25 is
based on the assumption that the
airplane is equipped with a control
system in which there is a direct
mechanical linkage between the pilot’s
cockpit control and the control surface.
Thus for roll maneuvers, the regulation
specifies a displacement for the aileron
itself, and does not envision any
modification of the pilot’s control input.
Since such a system will affect the
airplane flight loads and thus the
structural strength of the airplane,
special conditions appropriate for this
type of control system are needed.
In particular, the special condition
adjusts the design roll maneuver
requirements specified in § 25.349(a), so
that they take into account the effect of
the A380’s electronic flight control
computer on the control surface
deflection. The special condition
requires that the roll maneuver be
performed by deflection of the cockpit
roll control, as opposed to specifying a
deflection of the aileron itself as the
current regulation does. The deflection
of the control surface would then be
determined from the cockpit input,
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Fmt 4700
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based on the computer’s flight control
laws and the current airplane flight
parameters.
Discussion of Comments
Notice of Proposed Special
Conditions No. 25–06–01–SC,
pertaining to design roll maneuver for
the Airbus A380 airplane, was
published in the Federal Register on
March 29, 2006. A single comment
which supports the intent and language
of the special conditions, as proposed,
was received from the Airline Pilots
Association (ALPA). Accordingly, the
special conditions are adopted, 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.
I The authority citation for these
special conditions is as follows:
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 lieu of compliance with 14 CFR
25.349(a), the following special
condition applies:
The following conditions, speeds, and
cockpit roll control motions (except as
the motions may be limited by pilot
effort) must be considered in
combination with an airplane load
factor of zero and two-thirds of the
positive maneuvering factor used in
design. In determining the resulting
control surface deflections, the torsional
flexibility of the wing must be
considered in accordance with
§ 25.301(b):
a. Conditions corresponding to steady
rolling velocities must be investigated.
In addition, conditions corresponding to
maximum angular acceleration must be
investigated for airplanes with engines
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07JYR1
Federal Register / Vol. 71, No. 130 / Friday, July 7, 2006 / Rules and Regulations
Federal Aviation Administration
could be the origin of cracks that
developed in the fuselage skin and
propagated from the edge of the air vent
hole. We are issuing this AD to prevent
fatigue cracking of the fuselage skin,
which could result in loss of the
structural integrity of the fuselage and
consequent rapid depressurization of
the airplane.
DATES: This AD becomes effective
August 11, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 11, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–1622; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Examining the Docket
[Docket No. FAA–2006–24367; Directorate
Identifier 2006–NM–041–AD; Amendment
39–14677; AD 2006–14–06]
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
or other weight concentrations outboard
of the fuselage. For the angular
acceleration conditions, zero rolling
velocity may be assumed in the absence
of a rational time history investigation
of the maneuver.
b. At VA, sudden movement of the
cockpit roll control up to the limit is
assumed. The position of the cockpit
roll control must be maintained, until a
steady roll rate is achieved and then
must be returned suddenly to the
neutral position.
c. At VC, the cockpit roll control must
be moved suddenly and maintained so
as to achieve a roll rate not less than
that obtained in paragraph b. above.
d. At VD, the cockpit roll control must
be moved suddenly and maintained so
as to achieve a roll rate not less than one
third of that obtained in paragraph b.
above.
Issued in Renton, Washington, on June 29,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–10673 Filed 7–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 F4–600R Series Airplanes and
Model A300 C4–605R Variant F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
cprice-sewell on PROD1PC66 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 F4–600R series
airplanes and Model A300 C4–605R
Variant F airplanes. This AD requires
modifying certain structure in the
fuselage zone at the lavatory venturi
installation in the nose section, and
performing a related investigative action
and corrective action if necessary. This
AD results from an analysis that
revealed that airplanes equipped with
Airbus Modification 08909 had a
concentration of loads higher than
expected in the fuselage zone (high
stress) at the lavatory venturi
installation in the nose section, which
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15:33 Jul 06, 2006
Jkt 208001
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Airbus Model A300 F4–
600R series airplanes and Model A300
C4–605R Variant F airplanes. That
NPRM was published in the Federal
Register on April 11, 2006 (71 FR
18237). That NPRM proposed to require
modifying certain structure in the
fuselage zone at the lavatory venturi
installation in the nose section, and
performing a related investigative action
and corrective action if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
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38515
considered the single comment
received.
Request To Add Revised Service
Information
The manufacturer, Airbus, advises
that the service bulletin specified in the
NPRM has been revised. Airbus notes
that Airbus Service Bulletin A300–53–
6151, Revision 01, dated April 21, 2006,
contains minor changes and that no
additional work is required.
We agree with Airbus. We have
reviewed Revision 01 of the service
bulletin and agree that it does not
necessitate additional work. We have
revised paragraphs (f) and (g) of the AD
to reflect the revised service bulletin. In
addition, we have added a new
paragraph (h) to this AD specifying that
accomplishment of the actions specified
in paragraph (f) of the AD in accordance
with the original issue of the service
bulletin is considered to be an
acceptable method of compliance.
Subsequent paragraphs of the AD have
been re-identified accordingly.
Revision 01 also includes a reduced
cost for parts and we have revised the
Costs of Compliance section of the AD
to reflect that reduced cost.
Explanation of Change to This Final
Rule
Paragraph (g) of the NPRM specifies
making repairs using a method
approved by either the FAA or the
´ ´
Direction Generale de l’Aviation Civile
(or its delegated agent). The European
Aviation Safety Agency (EASA) has
assumed responsibility for the airplane
models subject to this AD. Therefore, we
have revised paragraph (g) of this AD to
specify making repairs using a method
approved by either the FAA or the
EASA (or its delegated agent).
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. These changes will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
This AD affects about 86 airplanes of
U.S. registry. The modification
(including the inspection) takes about
28 work hours per airplane, at an
average labor rate of $80 per work hour.
Required parts cost about $399 per
airplane. Based on these figures, the
estimated cost of the AD for U.S.
operators is $226,954, or $2,639 per
airplane.
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07JYR1
Agencies
[Federal Register Volume 71, Number 130 (Friday, July 7, 2006)]
[Rules and Regulations]
[Pages 38513-38515]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-10673]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM340; Special Conditions No. 25-318-SC]
Special Conditions: Airbus Model A380-800 Airplane, Design Roll
Maneuver
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 for design roll
maneuvers. 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 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 June 29, 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
[[Page 38514]]
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
The A380 is equipped with an electronic flight control system. In
this system, there is not a direct mechanical link between the airplane
flight control surface and the pilot's cockpit control device as there
is on more conventional airplanes. Instead, a flight control computer
commands the airplane flight control surfaces, based on input received
from the cockpit control device. The pilot input is modified by the
flight control computer--based on the current airplane flight
parameters before the command is given to the flight control surface.
Therefore, there is not a direct mechanical relationship between the
pilot command and the command given to the control surface.
The formulation of airplane design load conditions in 14 CFR part
25 is based on the assumption that the airplane is equipped with a
control system in which there is a direct mechanical linkage between
the pilot's cockpit control and the control surface. Thus for roll
maneuvers, the regulation specifies a displacement for the aileron
itself, and does not envision any modification of the pilot's control
input. Since such a system will affect the airplane flight loads and
thus the structural strength of the airplane, special conditions
appropriate for this type of control system are needed.
In particular, the special condition adjusts the design roll
maneuver requirements specified in Sec. 25.349(a), so that they take
into account the effect of the A380's electronic flight control
computer on the control surface deflection. The special condition
requires that the roll maneuver be performed by deflection of the
cockpit roll control, as opposed to specifying a deflection of the
aileron itself as the current regulation does. The deflection of the
control surface would then be determined from the cockpit input, based
on the computer's flight control laws and the current airplane flight
parameters.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-06-01-SC, pertaining
to design roll maneuver for the Airbus A380 airplane, was published in
the Federal Register on March 29, 2006. A single comment which supports
the intent and language of the special conditions, as proposed, was
received from the Airline Pilots Association (ALPA). Accordingly, the
special conditions are adopted, 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 lieu of compliance with 14 CFR 25.349(a), the following special
condition applies:
The following conditions, speeds, and cockpit roll control motions
(except as the motions may be limited by pilot effort) must be
considered in combination with an airplane load factor of zero and two-
thirds of the positive maneuvering factor used in design. In
determining the resulting control surface deflections, the torsional
flexibility of the wing must be considered in accordance with Sec.
25.301(b):
a. Conditions corresponding to steady rolling velocities must be
investigated. In addition, conditions corresponding to maximum angular
acceleration must be investigated for airplanes with engines
[[Page 38515]]
or other weight concentrations outboard of the fuselage. For the
angular acceleration conditions, zero rolling velocity may be assumed
in the absence of a rational time history investigation of the
maneuver.
b. At VA, sudden movement of the cockpit roll control up
to the limit is assumed. The position of the cockpit roll control must
be maintained, until a steady roll rate is achieved and then must be
returned suddenly to the neutral position.
c. At VC, the cockpit roll control must be moved
suddenly and maintained so as to achieve a roll rate not less than that
obtained in paragraph b. above.
d. At VD, the cockpit roll control must be moved
suddenly and maintained so as to achieve a roll rate not less than one
third of that obtained in paragraph b. above.
Issued in Renton, Washington, on June 29, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-10673 Filed 7-6-06; 8:45 am]
BILLING CODE 4910-13-P