[Federal Register: October 17, 2003 (Volume 68, Number 201)]
[Rules and Regulations]
[Page 59711-59713]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17oc03-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-353-AD; Amendment 39-13341; AD 2003-21-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330-301, -321, -322, -341, and -342
airplanes. This action requires modifying the rear fuselage to
reinforce a certain frame segment. This action is necessary to prevent
fatigue cracking of the rear fuselage, which could result in reduced
structural integrity of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective November 3, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 3, 2003.
Comments for inclusion in the Rules Docket must be received on or
before November 17, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-353-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address: 9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2001-NM-353-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
The service information referenced in this AD may be obtained from
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France. This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France, notified the FAA that an unsafe condition may exist on certain
Airbus Model A330-301, -321, -322, -341, and -342 airplanes. The DGAC
advises that, during fatigue testing, after 57,457 simulated flights, a
crack initiated and propagated in the rear fuselage on the right-hand
side of the airplane in the web of frame 65 at stringer 27, at the
first lower rivet row of the cross-beam attach fitting. Such cracking,
if not corrected, could result in reduced structural integrity of the
airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A330-53-3059, Revision 01, dated
October 15, 1997. That service bulletin describes procedures for
modifying the rear fuselage to reinforce frame 65 in the area of
stringer 27 at the first lower rivet row of the cross-beam attach
fitting. This modification includes performing rotating probe
inspections for cracking of certain fastener holes, reaming certain
fastener holes (either as a corrective action if cracking is found in
certain areas, or as a follow-on action for uncracked fastener holes),
cold-expanding certain fastener holes, replacing certain existing
fasteners with improved fasteners, and applying sealant. Accomplishment
of the actions specified in the service bulletin is intended to
adequately address the identified unsafe condition. The DGAC classified
this service bulletin as mandatory and issued French airworthiness
directive 2001-496(B), dated October 17, 2001, to ensure the continued
airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
[[Page 59712]]
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design that may be
registered in the United States at some time in the future, this AD is
being issued to prevent fatigue cracking of the rear fuselage, which
could result in reduced structural integrity of the airplane. This AD
requires accomplishment of the actions specified in the service
bulletin described previously, except as discussed below.
Differences Between This AD and Service Bulletin
Although the service bulletin specifies that operators may contact
the manufacturer for disposition of certain repair conditions, this AD
requires operators to repair those conditions per a method approved by
either the FAA or the DGAC (or its delegated agent). In light of the
type of repair that is required to address the unsafe condition, and
consistent with existing bilateral airworthiness agreements, we have
determined that, for this AD, a repair approved by either the FAA or
the DGAC would be acceptable for compliance with this AD.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 3 work hours to
accomplish the required actions, at an average labor rate of $65 per
work hour. Required parts would cost approximately $120 per airplane.
Based on these figures, the cost impact of this AD would be $315 per
airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
rule by submitting such written data, views, or arguments as they may
desire. Communications shall identify the Rules Docket number and be
submitted in triplicate to the address specified under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2001-NM-353-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-21-06 Airbus: Amendment 39-13341. Docket 2001-NM-353-AD.
Applicability: Model A330-301, -321, -322, -341, and -342
airplanes; certificated in any category; except those on which
Airbus Modification 43761, 44203, or 44052 has been accomplished in
production.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the rear fuselage, which could
result in reduced structural integrity of the airplane, accomplish
the following:
Service Bulletin Reference
(a) The following information pertains to the service bulletin
referenced in this AD:
[[Page 59713]]
(1) The term ``service bulletin'' as used in this AD, means the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3059,
Revision 01, dated October 15, 1997.
(2) Modifications accomplished before the effective date of this
AD per Airbus Service Bulletin A330-53-3059, dated June 18, 1996,
are acceptable for compliance with this AD.
Modification
(b) Prior to the accumulation of 20,000 total flight cycles,
modify the rear fuselage to reinforce frame 65 in the area of
stringer 27 at the first lower rivet row of the cross-beam attach
fitting (including performing rotating probe inspections for
cracking of certain fastener holes; accomplishing any applicable
repair; and replacing certain fasteners with new, improved
fasteners) by accomplishing all actions specified in paragraphs 2.A.
through 2.D. of the service bulletin. Do the actions per the service
bulletin, except as required by paragraph (c) of this AD. Any
applicable repair must be accomplished prior to further flight.
Repairs
(c) If any crack is found during any inspection required by this
AD, and the service bulletin recommends contacting Airbus for
appropriate action: Before further flight, repair per a method
approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated
agent).
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Airbus Service Bulletin A330-53-3059,
Revision 01, dated October 15, 1997. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
Note 1: The subject of this AD is addressed in French
airworthiness directive 2001-496(B), dated October 17, 2001.
Effective Date
(f) This amendment becomes effective on November 3, 2003.
Issued in Renton, Washington, on October 9, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-26117 Filed 10-16-03; 8:45 am]
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