AD 2004-06-11

[Federal Register Volume 69, Number 59 (Friday, March 26, 2004)]
[Rules and Regulations]
[Pages 15664-15666]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-6578]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-380-AD; Amendment 39-13537; AD 2004-06-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Series Airplanes; and Model A340-211, -212, 213, -311, -
312, and -313 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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 
series airplanes; and certain Model A340 series airplanes, that 
requires inspecting for and repairing cracking of

[[Page 15665]]

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: Effective April 30, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 30, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an 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 was published in the Federal Register on November 28, 
2003 (68 FR 66762). That action proposed to 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.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Revise Applicability

    The commenter requests that the applicability of the proposed AD be 
revised to match the applicability of the French airworthiness 
directive, which limits Model A340 series airplanes to A340-211, -212, 
213, -311, -312, and -313. The commenter states that the proposed (FAA) 
AD, as written, would include Model A340-500 and -600 series airplanes, 
which do not need the compliance check.
    We agree, for the reasons provided by the commenter. We have 
revised the applicability accordingly in this final rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    This AD will affect about 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 actions will take about 30 
work hours per airplane, at an average labor rate of $65 per work hour. 
Required parts will cost about $1,075 per airplane. Based on these 
figures, the cost impact of this AD 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 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 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:

2004-06-11 Airbus: Amendment 39-13537. 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 Airbus
               Model--                               modification--                 Or Airbus service bulletin--
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A330-301, -321, -322, -341, and -342   43503.....................................  A330-57-3055, dated November
 series airplanes.                                                                  28, 2001, or Revision 01,
                                                                                    dated May 2, 2002.
A340-211, -212, 213, -311, -312, and - 43692.....................................  A340-57-4062, dated November
 313 series airplanes.                                                              28, 2001, or Revision 01,
                                                                                    dated May 2, 2002.
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[[Page 15666]]

    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.
    (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 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 must be 
done in accordance with Airbus Service Bulletin A330-57-3055, 
Revision 01, dated May 2, 2002; or Airbus Service Bulletin A340-57-
4062, Revision 01, dated May 2, 2002; as applicable. 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, 1 Rond Point Maurice 
Bellonte, 31701 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 directives 2001-578(B) and 2001-579(B), both dated 
November 28, 2001.

Effective Date

    (f) This amendment becomes effective on April 30, 2004.

    Issued in Renton, Washington, on March 17, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6578 Filed 3-25-04; 8:45 am]
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