[Federal Register: November 28, 2003 (Volume 68, Number 229)]
[Proposed Rules]
[Page 66762-66764]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28no03-20]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 66762]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-380-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Series Airplanes; and Model A340 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A330-301, -
321, -322, -341, and -342 series airplanes; and certain Model A340
series airplanes. This proposal would require inspecting for and
repairing cracks of the wire harness slots in the inner rear spars of
the wings between ribs 4 and 5, and cold-expanding crack-free wire
harness slots and bolt holes. This action is necessary to prevent
cracking of the wire harness slot, which could result in reduced
structural integrity of the wing. This action is intended to address
the identified unsafe condition.
DATES: Comments must be received by December 29, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-380-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-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2001-NM-380-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus, 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.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
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 proposed
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 proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2001-NM-380-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2001-NM-380-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
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 series airplanes; and certain Model A340 series
airplanes. The DGAC advises that major wing fatigue tests revealed
cracks initiating from the wire harness slot in the inner rear spars of
the wings between ribs 4 and 5. The cracking can occur on airplanes
that have not been modified to reinforce the wire harness slot and the
adjacent holes. The results indicate that the fatigue life for the wire
harness slot is less than the design requirement. Cracks in the wire
harness slot, if not corrected, could result in reduced structural
integrity of the wing.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A330-57-3055 and A340-57-4062,
both Revision 01, dated May 2, 2002. The service bulletins describe
procedures for a modification of the inner rear spars of the wings. The
modification involves an eddy current surface crack inspection of the
wire harness slots in the rear spars of the wings between ribs 4 and 5,
a high-frequency eddy current rototest inspection for cracks in the
area around the bolt holes that attach the support plates of the
electrical connectors, and cold-expansion of the wire harness slots and
the bolt holes. The service bulletins recommend contacting Airbus if
cracks are found. Accomplishment of the actions specified in the
service bulletins is intended to adequately address the identified
unsafe condition. The DGAC
[[Page 66763]]
classified these service bulletins as mandatory and issued French
airworthiness directives 2001-578(B) and 2001-579(B), both dated
November 28, 2001, to ensure the continued airworthiness of these
airplanes in France.
FAA's Conclusions
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. 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 Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletins described previously,
except as discussed below.
Difference Between Proposed AD and Service Bulletins
Although the service bulletins specify that operators may contact
the manufacturer for disposition of certain repair conditions, this
proposal would require 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 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
approved by either the FAA or the DGAC would be acceptable for
compliance with this proposed AD.
Cost Impact
We estimate that this proposed AD would affect 1 Model A330 series
airplane of U.S. registry. Currently, there are no affected Model A330-
341 or A340 series airplanes on the U.S. Register. The proposed actions
would take about 30 work hours per airplane, at an average labor rate
of $65 per work hour. Required parts would cost about $1,075 per
airplane. Based on these figures, the cost impact of this proposed
action is estimated to be $3,025 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus: Docket 2001-NM-380-AD.
Applicability: The airplanes listed in Table 1 of this AD,
certificated in any category:
Table 1.--Applicability
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Except those
modified by Or Airbus Service
Model-- Airbus Bulletin--
Modification--
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A330-301, -321, -322, -341, and - 43503 A330-57-3055, dated
342 series airplanes. November 28, 2001,
or Revision 01,
dated May 2, 2002.
A340 series airplanes............. 43692 A340-57-4062, dated
November 28, 2001,
or Revision 01,
dated May 2, 2002.
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Compliance: Required as indicated, unless accomplished
previously.
To prevent cracking of the wire harness slot on the inner rear
spar of the wing, which could result in reduced structural integrity
of the wing, accomplish the following:
Modification
(a) At the time specified in paragraph (a)(1), (a)(2), or (a)(3)
of this AD: Modify the inner rear spars of the wings in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-57-3055 or A340-57-4062, both Revision 01, both dated May 2,
2002, as applicable. The modification involves an eddy current
surface crack inspection of the wire harness slots in the rear spars
of the wings between ribs 4 and 5, a high-frequency eddy current
rototest inspection for cracks in the area around the bolt holes
that attach the support plates of the electrical connectors, and
cold-expansion of the wire harness slots and the bolt holes.
[[Page 66764]]
(1) For Model A330 series airplanes: Inspect before the
accumulation of 16,500 total flight cycles or 51,400 total flight
hours, whichever occurs first.
(2) For Model A340 series airplanes, pre-Modification 41300:
Inspect before the accumulation of 14,500 total flight cycles or
75,400 total flight hours, whichever occurs first.
(3) For Model A340 series airplanes, post-Modification 41300:
Inspect before the accumulation of 13,400 total flight cycles or
70,000 total flight hours, whichever occurs first.
(b) A modification done before the effective date of this AD in
accordance with Airbus Service Bulletin A330-57-3055 or A340-57-
4062, both dated November 28, 2001, is acceptable for compliance
with the applicable requirements of this AD.
Repair
(c) If any crack is found during an inspection required by
paragraph (a) of this AD: Before further flight, repair in
accordance with 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
(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.
Note 1:
The subject of this AD is addressed in French airworthiness
directives 2001-578(B) and 2001-579(B), both dated November 28,
2001.
Issued in Renton, Washington, on November 21, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-29696 Filed 11-26-03; 8:45 am]
BILLING CODE 4910-13-P