Airworthiness Directives; Airbus Model A300 F4-600R Series Airplanes and Model A300 C4-605R Variant F Airplanes, 18237-18239 [E6-5246]
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Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
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.
Discussion of Novel or Unusual Design
Features
The A380 will have a flightdeck
bulkhead which is reinforced to resist
intrusion and ballistic penetration. On
January 15, 2002, the FAA promulgated
14 CFR 25.795(a), which specifies that
the flightdeck door installation be
designed to resist forcible intrusion by
unauthorized persons or penetration by
small arms fire and fragmentation
devices. The regulation was limited to
the flightdeck door to expedite a rapid
retrofit of existing airplanes which are
required by operating rules to have a
flightdeck door.
The FAA intends that the flightdeck
bulkhead—and any other accessible
barrier separating the flightcrew
compartment from occupied areas—also
be designed to resist intrusion or
penetration. We are in the process of
rulemaking to amend § 25.795(a) to
make that and other changes pertaining
to security.
Meanwhile, the FAA is proposing
special conditions for the Airbus Model
A380–800 regarding design of the
reinforced flightdeck bulkhead
separating the flightcrew compartment
from occupied areas. The special
conditions would require that the
flightdeck bulkhead meet the same
standards as those specified in
§ 25.795(a) for flightdeck doors. For the
A380, the bulkhead may be comprised
of components, such as lavatory and
crew rest walls; these components are
covered by these special conditions.
hsrobinson on PROD1PC70 with PROPOSALS
Applicability
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 condition as part of
the type certification basis for the
Airbus A380–800 airplane.
In addition to the requirements of 14
CFR 25.795(a) governing protection of
the flightdeck door, the following
special conditions apply:
The bulkhead, including components
that comprise the bulkhead, separating
the flightcrew compartment from
occupied areas must be designed to
meet the following standards:
• It must resist forcible intrusion by
unauthorized persons and be capable of
withstanding impacts of 300 Joules
(221.3 foot-pounds) at critical locations
as well as a 1113 Newton (250 pound)
constant tensile load on accessible
handholds, including the doorknob or
handle.
• It must resist penetration by small
arms fire and fragmentation devices to
a level equivalent to level IIIa of the
National Institute of Justice Standard
(NIJ) 0101.04.
Issued in Renton, Washington, on April 3,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–5240 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
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.
[Docket No. FAA–2006–24367; Directorate
Identifier 2006–NM–041–AD]
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: Notice of proposed rulemaking
(NPRM).
AGENCY:
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.
VerDate Aug<31>2005
List of Subjects in 14 CFR Part 25
15:25 Apr 10, 2006
Jkt 208001
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
18237
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Model A300 F4–600R
series airplanes and Model A300 C4–
605R Variant F airplanes. This proposed
AD would 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. This proposed 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 could be the origin of
cracks that developed in the fuselage
skin and propagated from the edge of
the air vent hole. We are proposing 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: We must receive comments on
this proposed AD by May 11, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
E:\FR\FM\11APP1.SGM
11APP1
18238
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
number ‘‘FAA–2006–24367; Directorate
Identifier 2006–NM–041–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
hsrobinson on PROD1PC70 with PROPOSALS
Discussion
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Model A300 F4–600R
series airplanes and Model A300 C4–
605R Variant F airplanes. The DGAC
advises that analysis 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 area
between frame (FR) 12 and FR 12A on
the left-hand side of the nose section,
which could be the origin of cracks that
developed in the fuselage skin and
propagated from the edge of the air vent
hole. This condition, if not corrected,
could result in loss of the structural
integrity of the fuselage and consequent
rapid depressurization of the airplane.
VerDate Aug<31>2005
15:25 Apr 10, 2006
Jkt 208001
Relevant Service Information
Airbus has issued Service Bulletin
A300–53–6151, dated December 2,
2005. The service bulletin describes
procedures for modifying certain
structure in the fuselage zone at the
lavatory venturi installation area
between FR 12 and FR 12A on the lefthand side of the nose section, and
performing a related investigative action
and corrective action if necessary. The
related investigative action is a high
frequency eddy current inspection of
the skin panel cutout for cracking. The
corrective action in the service bulletin
recommends contacting Airbus for
instructions for crack repair.
The DGAC mandated the service
information and issued French
airworthiness directive F–2006–030,
dated February 1, 2006, to ensure the
continued airworthiness of these
airplanes in France.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the DGAC has
kept the FAA informed of the situation
described above. We have examined the
DGAC’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for airplanes of this
type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Among Proposed AD, French
Airworthiness Directive, and Service
Information.’’
Differences Among Proposed AD,
French Airworthiness Directive, and
Service Information
The service bulletin specifies that you
may contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD
requires you to repair those conditions
using a method that we or the DGAC (or
its delegated agent) approve. In light of
the type of repair that would be required
to address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair we or the DGAC (or its
delegated agent) approve is acceptable
for compliance with this proposed AD.
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
The applicability of the French
airworthiness directive excludes
airplanes on which Airbus Service
Bulletin A300–53–6151 was
accomplished in service. However, we
have not excluded those airplanes in the
applicability of this proposed AD;
rather, this proposed AD includes a
requirement to accomplish the actions
specified in that service bulletin. This
requirement would ensure that the
actions specified in the service bulletin
and required by this proposed AD are
accomplished on all affected airplanes.
Operators must continue to operate the
airplane in the configuration required
by this proposed AD unless an
alternative method of compliance is
approved.
Costs of Compliance
This proposed AD would affect about
86 airplanes of U.S. registry. The
proposed modification (including the
inspection) would take about 28 work
hours per airplane, at an average labor
rate of $80 per work hour. Required
parts would cost about $1,260 per
airplane. Based on these figures, the
estimated cost of the proposed AD for
U.S. operators is $301,000, or $3,500 per
airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
E:\FR\FM\11APP1.SGM
11APP1
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA–2006–24367;
Directorate Identifier 2006–NM–041–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by May 11, 2006.
Affected ADs
(b) None.
hsrobinson on PROD1PC70 with PROPOSALS
Unsafe Condition
(d) 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 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
15:25 Apr 10, 2006
Jkt 208001
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
(f) Before the accumulation of 16,900 total
flight cycles since first flight of the airplane:
Modify the fuselage zone at the lavatory
venturi installation area between frame (FR)
12 and FR 12A on the left-hand side of the
nose section and do the related investigative
action by accomplishing all the actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
53–6151, dated December 2, 2005.
Corrective Action
(g) If any crack is found during the
inspection required by this AD and Airbus
Service Bulletin A300–53–6151, dated
December 2, 2005, specifies to contact Airbus
for crack repair: Before further flight, repair
the crack using a method approved by either
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
´ ´
the Direction Generale de l’Aviation Civile
(or its delegated agent).
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(i) French airworthiness directive F–2006–
030, dated February 1, 2006, also addresses
the subject of this AD.
Issued in Renton, Washington, on March
30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–5246 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
Frm 00009
Federal Aviation Administration
Fmt 4702
Sfmt 4702
[Docket No. FAA–2006–24365; Directorate
Identifier 2006–NM–022–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Modification/Investigative Action
PO 00000
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
Compliance
Related Information
Applicability
(c) This AD applies to Airbus Model A300
F4–605R and F4–622R airplanes and Model
A300 C4–605R Variant F airplanes,
certificated in any category; on which Airbus
Modification 08909 has been done in
production; except airplanes on which
Airbus Modification 12980 has been done in
production.
VerDate Aug<31>2005
skin, which could result in loss of the
structural integrity of the fuselage and
consequent rapid depressurization of the
airplane.
18239
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–400
series airplanes. This proposed AD
would require repetitive inspections for
cracks of the first fuel access panel
outboard of the nacelle on the left- and
right-hand wings, and related
investigative/corrective actions if
necessary. This proposed AD also
would require eventual replacement of
each access panel with a new access
panel having a new part number. The
replacement would terminate the
repetitive inspection requirements. This
proposed AD results from reports of
cracks of the fuel access panels. We are
proposing this AD to detect and correct
cracked fuel access panels, which could
lead to arcing and ignition of fuel vapor
during a lightning strike, and result in
fuel tank explosions and consequent
loss of the airplane.
DATES: We must receive comments on
this proposed AD by May 11, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed AD.
E:\FR\FM\11APP1.SGM
11APP1
]]>Agencies
[Federal Register Volume 71, Number 69 (Tuesday, April 11, 2006)]
[Proposed Rules]
[Pages 18237-18239]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-5246]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24367; Directorate Identifier 2006-NM-041-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 F4-600R Series
Airplanes and Model A300 C4-605R Variant F Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A300 F4-600R series airplanes and Model A300
C4-605R Variant F airplanes. This proposed AD would 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. This proposed
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 could be the origin of cracks
that developed in the fuselage skin and propagated from the edge of the
air vent hole. We are proposing 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: We must receive comments on this proposed AD by May 11, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket
[[Page 18238]]
number ``FAA-2006-24367; Directorate Identifier 2006-NM-041-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Model A300 F4-600R series
airplanes and Model A300 C4-605R Variant F airplanes. The DGAC advises
that analysis 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 area between
frame (FR) 12 and FR 12A on the left-hand side of the nose section,
which could be the origin of cracks that developed in the fuselage skin
and propagated from the edge of the air vent hole. This condition, if
not corrected, could result in loss of the structural integrity of the
fuselage and consequent rapid depressurization of the airplane.
Relevant Service Information
Airbus has issued Service Bulletin A300-53-6151, dated December 2,
2005. The service bulletin describes procedures for modifying certain
structure in the fuselage zone at the lavatory venturi installation
area between FR 12 and FR 12A on the left-hand side of the nose
section, and performing a related investigative action and corrective
action if necessary. The related investigative action is a high
frequency eddy current inspection of the skin panel cutout for
cracking. The corrective action in the service bulletin recommends
contacting Airbus for instructions for crack repair.
The DGAC mandated the service information and issued French
airworthiness directive F-2006-030, dated February 1, 2006, to ensure
the continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Among
Proposed AD, French Airworthiness Directive, and Service Information.''
Differences Among Proposed AD, French Airworthiness Directive, and
Service Information
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD requires you to repair those conditions using a method
that we or the DGAC (or its delegated agent) approve. In light of the
type of repair that would be required to address the unsafe condition,
and consistent with existing bilateral airworthiness agreements, we
have determined that, for this proposed AD, a repair we or the DGAC (or
its delegated agent) approve is acceptable for compliance with this
proposed AD.
The applicability of the French airworthiness directive excludes
airplanes on which Airbus Service Bulletin A300-53-6151 was
accomplished in service. However, we have not excluded those airplanes
in the applicability of this proposed AD; rather, this proposed AD
includes a requirement to accomplish the actions specified in that
service bulletin. This requirement would ensure that the actions
specified in the service bulletin and required by this proposed AD are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this proposed AD
unless an alternative method of compliance is approved.
Costs of Compliance
This proposed AD would affect about 86 airplanes of U.S. registry.
The proposed modification (including the inspection) would take about
28 work hours per airplane, at an average labor rate of $80 per work
hour. Required parts would cost about $1,260 per airplane. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $301,000, or $3,500 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
[[Page 18239]]
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-24367; Directorate Identifier 2006-NM-
041-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by May 11,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 F4-605R and F4-622R
airplanes and Model A300 C4-605R Variant F airplanes, certificated
in any category; on which Airbus Modification 08909 has been done in
production; except airplanes on which Airbus Modification 12980 has
been done in production.
Unsafe Condition
(d) 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 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.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Modification/Investigative Action
(f) Before the accumulation of 16,900 total flight cycles since
first flight of the airplane: Modify the fuselage zone at the
lavatory venturi installation area between frame (FR) 12 and FR 12A
on the left-hand side of the nose section and do the related
investigative action by accomplishing all the actions specified in
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6151, dated December 2, 2005.
Corrective Action
(g) If any crack is found during the inspection required by this
AD and Airbus Service Bulletin A300-53-6151, dated December 2, 2005,
specifies to contact Airbus for crack repair: Before further flight,
repair the crack using a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent).
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(i) French airworthiness directive F-2006-030, dated February 1,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on March 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-5246 Filed 4-10-06; 8:45 am]
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