[Federal Register Volume 68, Number 229 (Friday, November 28, 2003)]
[Proposed Rules]
[Pages 66762-66764]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29696]


 ========================================================================
 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.
 
 ========================================================================
 

  Federal Register / Vol. 68, No. 229 / Friday, November 28, 2003 / 
Proposed Rules  

[[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).

-----------------------------------------------------------------------

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: 
[email protected]. 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
------------------------------------------------------------------------
                                     Except those
                                      modified by     Or Airbus Service
              Model--                   Airbus           Bulletin--
                                    Modification--
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

    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