AD 2000-19-06

[Federal Register Volume 65, Number 183 (Wednesday, September 20, 2000)]
[Rules and Regulations]
[Pages 56785-56788]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-23999]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-43-AD; Amendment 39-11907; AD 2000-19-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and 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), 
applicable to certain Airbus Model A330 and A340 series airplanes. This 
action requires modifying the bottom skin panel 3 (located aft of the 
rear spar). This action is necessary to prevent corrosion and 
consequent reduced structural integrity of the wings due to lack of 
cold expansion of an existing drain hole, which could lead to cracks 
initiating from that drain hole; and the incorrect location of the 
drain hole, which can allow moisture to be trapped. This action is 
intended to address the identified unsafe condition.

DATES: Effective October 5, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 5, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before October 20, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-43-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#ae9783cfc0c383c7cfdccdc1c3c3cbc0daeec8cfcf80c9c1d8"><span class="__cf_email__" data-cfemail="85bca8e4ebe8a8ece4f7e6eae8e8e0ebf1c5e3e4e4abe2eaf3">[email&#160;protected]</span></a>. Comments

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sent via fax or the Internet must contain ``Docket No. 2000-NM-43-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 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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 and 
A340 series airplanes. The DGAC advises that cold expansion of the 
existing drain hole in bottom skin panel 3 (located aft of the rear 
spar) was not performed during manufacture of the airplane. Such lack 
of cold expansion could lead to cracks initiating from the drain hole. 
In addition, in-service experience has shown that the location of this 
drain hole traps moisture which results in corrosion. These conditions, 
if not corrected, could result in corrosion and consequent reduced 
structural integrity of the wings.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A330-57-3060 (for Model A330 
series airplanes) and A340-57-4068 (for Model A340 series airplanes), 
both Revision 01, both dated December 6, 1999. These service bulletins 
describe procedures for modifying the bottom skin panel 3 (located aft 
of the rear spar) on the left and right wings. The modification 
involves cold expanding the existing drain hole [including performing a 
high frequency eddy current (HFEC) rototest inspection of the drain 
hole for cracks, cold expanding the drain hole, and drilling and 
reaming the drain hole to a specific diameter]. The modification also 
entails adding another drain hole, if necessary (including drilling and 
reaming the new drain hole to a specific diameter, and cold expanding 
the drain hole).
    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 2000-158-119(B) and 2000-157-145(B), both 
dated April 5, 2000, in order to assure 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 the 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, this AD is being issued to prevent corrosion and 
consequent reduced structural integrity of the wings due to lack of 
cold expansion of an existing drain hole, which could lead to cracks 
initiating from that drain hole; and the incorrect location of the 
drain hole, which can allow moisture to be trapped. This AD requires 
accomplishment of the actions specified in the service bulletins 
described previously, except as discussed below.

Difference Between Service Bulletins and This AD

    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 in accordance with a method approved by the FAA.

Cost Impact

    Three of the Model A330 series airplanes affected by this action 
are on the U.S. Register; however, the FAA has been advised that the 
actions required by this AD have been accomplished on those airplanes. 
None of the Model A340 series airplanes affected by this action are on 
the U.S. Register. All Model A340 series airplanes included in the 
applicability of this rule 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 rule 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, it would require approximately 5 work hours to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$300 per airplane.

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

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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-43-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:

2000-19-06  Airbus Industrie: Amendment 39-11907. Docket 2000-NM-43-
AD.

    Applicability: Model A330-202, -223, -301, -321, and -322 series 
airplanes having manufacturer's serial numbers (MSN) 0012 through 
0244 inclusive; and Model A340-211, -212, -213, -311, -312, and -313 
series airplanes having MSN's 0002 through 0245 inclusive; 
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 (c) 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 corrosion and consequent reduced structural integrity 
of the wings due to lack of cold expansion of an existing drain 
hole, which could lead to cracks initiating from that drain hole; 
and the incorrect location of the drain hole, which can allow 
moisture to be trapped; accomplish the following:

Modification

    (a) Modify the bottom skin panel 3, located aft of the rear spar 
on the left and right wings, by cold expanding the existing drain 
hole [including performing a high frequency eddy current (HFEC) 
rototest inspection of the hole for cracks, cold expanding the hole, 
and drilling and reaming the hole to a specific diameter], and by 
adding another drain hole, as necessary (including drilling and 
reaming the new hole to a specific diameter, and cold expanding the 
hole). Accomplish the actions in accordance with Airbus Service 
Bulletin A330-57-3060 (for Model A330 series airplanes) or A340-57-
4068 (for Model A340 series airplanes), both Revision 01, both dated 
December 6, 1999; as applicable; at the time specified in paragraph 
(a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable.
    (1) For Model A330-202 and -223 series airplanes: Prior to the 
accumulation of 9,600 total landings or 32,600 total flight hours, 
whichever occurs first.
    (2) For Model A330-301, -321, and -322 series airplanes: Prior 
to the accumulation of 15,000 total landings or 51,000 total flight 
hours, whichever occurs first.
    (3) For Model A340-211, -212, -213, -311, -312, and -313 series 
airplanes on which Airbus Modification 41300 has NOT been 
accomplished prior to the effective date of this AD: Prior to the 
accumulation of 10,800 total landings or 48,000 total flight hours, 
whichever occurs first.
    (4) For Model A340-213 and -313 series airplanes on which Airbus 
Modification 41300 has been accomplished prior to the effective date 
of this AD: Prior to the accumulation of 8,100 total landings or 
36,000 total flight hours, whichever occurs first.

Certain Repairs

    (b) If any damage is found during accomplishment of the 
modification required by paragraph (a) of this AD, and the 
applicable service bulletin specifies to contact Airbus for 
appropriate action: Prior to further flight, repair in accordance 
with a method approved by the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate. For a repair method to be 
approved by the Manager, International Branch, ANM-116, as required 
by this paragraph, the Manager's approval letter must specifically 
reference this AD.

Alternative Methods of Compliance

    (c) 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, 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 2: 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

    (d) 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

    (e) Except as provided by paragraph (b) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A330-57-
3060, Revision 01, dated December 6, 1999; or Airbus Service 
Bulletin A340-57-4068, Revision 01, dated December 6, 1999; 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 3: The subject of this AD is addressed in French 
airworthiness directives 2000-158-119(B) and 2000-157-145(B), both 
dated April 5, 2000.

Effective Date

    (f) This amendment becomes effective on October 5, 2000.


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    Issued in Renton, Washington, on September 13, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-23999 Filed 9-19-00; 8:45 am]
BILLING CODE 4910-13-P