AD 2001-15-29

[Federal Register Volume 66, Number 150 (Friday, August 3, 2001)]
[Rules and Regulations]
[Pages 40582-40584]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-19259]



[[Page 40582]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-195-AD; Amendment 39-12364; AD 2001-15-29]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Series Airplanes and Airbus Model A340 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A330-301, -321, -322, and -342 
series airplanes and certain Airbus Model A340 series airplanes, that 
currently requires reinforcement of the wing structure at the inboard 
pylon rear pickup area. This amendment revises the applicability to 
include additional airplanes. The actions specified by this AD are 
intended to prevent fatigue cracking of the bottom skin and reinforcing 
plate of the wing due to bending, which could lead to reduced 
structural integrity of the airplane wing. This action is intended to 
address the identified unsafe condition.

DATES: Effective August 20, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of May 14, 2001 (66 FR 21074, April 27, 2001).
    Comments for inclusion in the rules docket must be received on or 
before September 4, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2001-NM-195-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: 
<a href="/cdn-cgi/l/email-protection#92abbff3fcffbffbf3e0f1fdfffff7fce6d2f4f3f3bcf5fde4"><span class="__cf_email__" data-cfemail="d0e9fdb1bebdfdb9b1a2b3bfbdbdb5bea490b6b1b1feb7bfa6">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-195-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 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: On April 19, 2001, the FAA issued AD 2001-
08-25, amendment 39-12202 (66 FR 21074, April 27, 2001). That AD is 
applicable to certain Airbus Model A330-301, -321, -322, and -342 
series airplanes and certain Airbus Model A340 series airplanes. That 
AD requires reinforcement of the wing structure at the inboard pylon 
rear pickup area. That AD was prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The requirements of that AD are intended to prevent fatigue 
cracking of the bottom skin and reinforcing plate of the wing due to 
bending, which could lead to reduced structural integrity of the 
airplane wing.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2001-08-25, the FAA has been advised by 
the manufacturer that Airbus Model A330-341 series airplanes should 
have been included in the applicability of that AD. The FAA has 
determined that Model A330-341 series airplanes were inadvertently 
omitted from the applicability of that AD.

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 21.19) and 
the applicable bilateral airworthiness agreement.

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 future time, this AD supersedes 
AD 2001-08-25 to continue to require reinforcement of the wing 
structure at the inboard pylon rear pickup area. This AD expands the 
applicability of the existing AD to include Model A330-341, which was 
inadvertently omitted from the existing 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 AD 
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 AD 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, for Model A330 series airplanes to follow 
Airbus Service Bulletin A330-57-3021, it would require approximately 
380 work hours to accomplish the required replacements, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $44,800 per airplane. Based on these figures, the 
expected cost of these replacements per airplane would be $67,600.
    Also for Model A330 series airplanes, to follow Airbus Service 
Bulletin A330-54-3005, it would require approximately 36 work hours to 
accomplish the required replacements, at an average labor rate of $60 
per work hour. Required parts would cost approximately $15,774 per 
airplane. Based on these figures, the expected cost of these 
replacements per airplane would be $17,934.
    For Airbus Model A340 series airplanes, to follow Airbus Service 
Bulletin A340-57-4025, it would require approximately 380 work hours to 
accomplish the required replacements, at an average labor rate of $60 
per work hour. Required parts would cost approximately $44,800 per 
airplane. Based on these figures, the expected cost of these 
replacements per airplane would be $67,600.
    Also for Model A340 series airplanes, to follow Airbus Service 
Bulletin A340-54-4003, it would require approximately 26 work hours to 
accomplish the required replacements, at an average labor rate of $60 
per work hour. Required parts would cost approximately $15,358 per 
airplane. Based on these figures, the expected cost of these 
replacements per airplane would be $16,918.

[[Page 40583]]

    The cost impact figures discussed above are 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.

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:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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 20011-NM-195-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

    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

    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 removing amendment 39-12202 (66 FR 
21074, April 27, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-12364, to read as follows:

2001-15-29  Airbus Industrie: Amendment 39-12364. Docket 2001-NM-
195-AD. Supersedes AD 2001-08-25, Amendment 39-12202.

    Applicability: Model A330-301, -321, -322, -341, and -342 series 
airplanes, as listed in Airbus Service Bulletin A330-57-3021, 
Revision 03, including Appendices 01 and 02, dated November 5, 1999; 
and Model A340 series airplanes, as listed in Airbus Service 
Bulletin A340-57-4025, Revision 02, including Appendices 01 and 02, 
dated November 5, 1999; certificated in any category.

    Note 1:
    This AD applies to each airplane identified in the preceding 
applicability provision, regardless of whether it has been modified, 
altered, or repaired in the area subject to the requirements of this 
AD. For airplanes that have been modified, altered, or repaired so 
that the performance of the requirements of this AD is affected, the 
owner/operator must request approval for an alternative method of 
compliance in accordance with paragraph (d) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if the unsafe condition has not been eliminated, the request 
should include specific proposed actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking of the airplane wing bottom skin and 
reinforcing plate due to wing bending, which could lead to reduced 
structural integrity of the wing, accomplish the following:

Modification

    (a) For Model A330 series airplanes, prior to the accumulation 
of 12,000 total flight cycles or 37,300 total flight hours, 
whichever occurs first, accomplish the actions required by 
paragraphs (a)(1) and (a)(2) of this AD.
    (1) Prior to, or concurrently with, the accomplishment of the 
tasks required by paragraph (a)(2) of this AD, replace five existing 
fillets with five new fillets, one existing firewall with one new 
firewall, and one existing case drainpipe with one new case 
drainpipe, and modify the contour milling of the external tip of rib 
19A on each of the left and right wing pylons, in accordance with 
Airbus Service Bulletin A330-54-3005, Revision 01, dated October 19, 
1999.
    (2) Concurrently with, or subsequent to, the accomplishment of 
the tasks required by paragraph (a)(1) of this AD, reinforce the 
wing structure at the inboard pylon rear pickup area on both wings 
(including performing high-frequency eddy current rototests, 
corrective actions if necessary, and installing a larger reinforcing 
plate and packer plate) in accordance with Airbus Service Bulletin 
A330-57-3021, Revision 03, including Appendices 01 and 02, dated 
November 5, 1999.
    (b) For Model A340 series airplanes, prior to the accumulation 
of 15,000 total flight cycles or 59,600 total flight hours, 
whichever occurs first, accomplish the actions required by 
paragraphs (b)(1) and (b)(2) of this AD.

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    (1) Prior to, or concurrently with, the accomplishment of the 
tasks required by paragraph (b)(2) of this AD, reinforce the wing 
structure at the inboard pylon rear pickup area of both wings 
(including performing high-frequency eddy current rototests, 
corrective actions if necessary, and installing a larger reinforcing 
plate and packer plate) in accordance with Airbus Service Bulletin 
A340-57-4025, Revision 02, including Appendices 01 and 02, dated 
November 5, 1999.
    (2) Concurrently with, or subsequent to, the accomplishment of 
the tasks required by paragraph (b)(1) of this AD, replace five 
existing fillets with five new fillets and one existing firewall 
with one new firewall on each of the left and right wing inboard 
pylons, in accordance with Airbus Service Bulletin A340-54-4003, 
Revision 01, dated April 26, 2000.
    (c) If any discrepancy is found during any inspection or 
rototest required by paragraphs (a)(2) or (b)(1) of this AD, prior 
to further flight, accomplish applicable repairs in accordance with 
Airbus Service Bulletin A330-57-3021, Revision 03, including 
Appendices 01 and 02, dated November 5, 1999 (for Model A330 series 
airplanes); or Airbus Service Bulletin A340-57-4025, Revision 02, 
including Appendices 01 and 02, dated November 5, 1999 (for Model 
A340 series airplanes). If the service bulletin specifies to contact 
the manufacturer for appropriate action: Prior to further flight, 
repair in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (or its delegated 
agent).

    Note 2: Accomplishment of the modifications required by 
paragraphs (a)(1) and (a)(2) or paragraphs (b)(1) and (b)(2) of this 
AD, prior to the effective date of this AD in accordance with the 
service bulletins listed in Table 1 of this AD, as follows, is 
considered acceptable for compliance with the applicable actions 
this AD:


                     Table 1.--Prior Service Bulletins Considered Acceptable for Compliance
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               Model                        Service bulletin             Revision level             Date
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A330..............................  A330-54-3005                     Original.............  March 25, 1996.
A330..............................  A330-57-3021                     Original.............  March 25, 1996.
                                    A330-57-3021                     01...................  September 1, 1998.
                                    A330-57-3021                     02...................  April 9, 1999.
A340..............................  A340-57-4025                     Original.............  March 25, 1996.
                                    A340-57-4025                     01...................  September 1, 1998.
A340..............................  A340-54-4003                     Original.............  March 25, 1996.
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Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and send it to the manager, International 
Branch ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the international Branch, ANM-116.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (f) Except as provided by paragraph (c) of this AD, the actions 
must be done in accordance with Airbus Service Bulletin A330-57-
3021, Revision 03, including Appendices 01 and 02, dated November 5, 
1999; Airbus Service Bulletin A340-57-4025, Revision 02, including 
Appendices 01 and 02, dated November 5, 1999; Airbus Service 
Bulletin A330-54-3005, Revision 01, dated October 19, 1999; and 
Airbus Service Bulletin A340-54-4003, Revision 01, dated April 26, 
2000; as applicable. This incorporation by reference was approved 
previously by the Director of the Federal Register as of May 14, 
2001 (66 FR 21074, April 27, 2001). 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 4: The subject of this AD is addressed in French 
airworthiness directives 2000-178-121(B) and 2000-179-147(B), both 
dated May 3, 2000.

Effective Date

    (g) This amendment becomes effective on August 20, 2001.

    Issued in Renton, Washington, on July 25, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-19259 Filed 8-2-01; 8:45 am]
BILLING CODE 4910-13-P