AD 2001-08-25

[Federal Register Volume 66, Number 82 (Friday, April 27, 2001)]
[Rules and Regulations]
[Pages 21074-21077]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-10338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-182-AD; Amendment 39-12202; AD 2001-08-25]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322, 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 adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A330-301, -321, -322, and -342 
series airplanes and certain Airbus Model A340 series airplanes. This 
action requires reinforcement of the wing structure at the inboard 
pylon rear pickup area. This action is necessary 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 May 14, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 14, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 29, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-182-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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#c4fde9a5aaa9e9ada5b6a7aba9a9a1aab084a2a5a5eaa3abb2"><span class="__cf_email__" data-cfemail="c7feeaa6a9aaeaaea6b5a4a8aaaaa2a9b387a1a6a6e9a0a8b1">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-182-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

[[Page 21075]]

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: 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: The Direction Generale 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, and -342 series airplanes and certain Airbus Model 
A340 series airplanes. The DGAC advises that, during wing fatigue 
tests, cracks were detected on the bottom skin and reinforcing plates 
of stringers 10 and 11 between ribs 10 and 10A at the inboard pylon 
rear pickup. This condition, if not corrected, could result in reduced 
structural integrity of the airplane wing.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A330-57-3021, Revision 03, 
including Appendices 01 and 02, (for Model A330 series airplanes), and 
A340-57-4025, Revision 02, including Appendices 01 and 02 (for Model 
A340 series airplanes), both dated November 5, 1999, which describe 
procedures for reinforcement of the wing structure at the inboard pylon 
rear pickup area. This involves removing the existing reinforcing 
plate; performing high-frequency eddy current tests for cracks, and 
corrective action, if necessary; and installing a larger reinforcing 
plate and packer plate. Accomplishment of the actions specified in the 
service bulletins is intended to adequately address the identified 
unsafe condition. The DGAC classified these service bulletins as 
mandatory and issued French airworthiness directives 2000-178-121(B) 
and 2000-179-147(B), both dated May 3, 2000, in order to assure the 
continued airworthiness of these airplanes in France.
    Airbus Service Bulletin A330-57-3021, Revision 03, including 
Appendices 01 and 02, dated November 5, 1999, specifies the prior or 
concurrent accomplishment of Airbus Service Bulletin A330-54-3005. 
Revision 01, dated October 19, 1999, of this service bulletin, 
describes procedures for replacing five existing fillets with five new 
fillets, one existing firewall with one new firewall, one existing case 
drainpipe with one new case drainpipe, and modifying the contour 
milling of the external tip of rib 19A on the left hand (LH) and right 
hand (RH) pylons.
    Airbus Service Bulletin A340-57-4025, Revision 02, including 
Appendices 01 and 02, dated November 5, 1999, specifies the prior or 
concurrent accomplishment of Airbus Service Bulletin A340-54-4003. 
Revision 01, dated April 26, 2000, of this service bulletin, describes 
procedures for replacing five existing fillets with five new fillets 
and one existing firewall with one new firewall on the LH and RH 
inboard pylons.

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. 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 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 is being 
issued to prevent fatigue cracking of the bottom skin and reinforcing 
plate of the airplane wings due to bending, which could lead to reduced 
structural integrity of the wings. This AD requires accomplishment of 
the actions specified in the service bulletins described previously, 
except as discussed below.

Differences Between Rule and Service Bulletins

    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this AD requires the repair of those conditions to 
be accomplished 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 identified unsafe condition, and in consonance 
with existing bilateral airworthiness agreements, the FAA has 
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 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 A330-301, -321, -322, and -342 series 
airplanes, to follow Airbus Service Bulletin A330-57-3021, Revision 03, 
including Appendices 01 and 02, dated November 5, 1999, 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 A330-301, -321, -322, and -342 series airplanes, to 
follow Airbus Service Bulletin A330-54-3005, Revision 01, dated October 
19, 1999, 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, Revision 02, including Appendices 01 and 02, 
dated November 5, 1999, 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, Revision 01, dated April 26, 2000, 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

[[Page 21076]]

expected cost of these replacements per airplane would be $16,918.

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 proposed 
AD is being requested.
    <bullet> Include justification (e.g.,<ls-thn-eq> 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 2000-NM-182-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 adding the following new 
airworthiness directive:

2001-08-25  Airbus Industrie: Amendment 39-12202. Docket 2000-NM-
182-AD.

    Applicability: Model A330-301, -321, -322, 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.
    (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

[[Page 21077]]

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) prior 
to the effective date of this AD in accordance with the service 
bulletins listed in Table 1, as follows, is considered acceptable 
for compliance with the applicable actions in 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............................  A330-57-3021                  Original...............  March 25, 1996.
                                  A330-57-3021                  01.....................  September 1, 1998.
                                  A330-57-3021                  02.....................  April 9, 1999.
A330............................  A330-54-3005                  Original...............  March 25, 1996.
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 then 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 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 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 May 14, 2001.

    Issued in Renton, Washington, on April 19, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-10338 Filed 4-26-01; 8:45 am]
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