[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13508-13510]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6947]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-22-AD; Amendment 39-10410]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Direct 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 A320-111 series airplanes. This 
amendment requires repetitive inspections to detect cracking around the 
attachment holes for the access panels in the lower skin of the wing; 
and repair, if necessary. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified in this AD are intended 
to detect and correct such cracking, which could result in reduced 
structural integrity of the airplane.

DATES: Effective June 18, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 18, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before April 20, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-

[[Page 13509]]

22-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
    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 A320-111 
series airplanes. The DGAC advises that it has received a report of 
cracking detected during fatigue testing on a test article; the cracks 
were found around the attachment holes for the access panels in the 
lower skin of the wing, between ribs 13 and 22. Such cracking, if not 
detected and corrected in a timely manner, could result in reduced 
structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-57-1056, Revision 1, dated 
July 15, 1997, including Appendix 1, which describes procedures for 
repetitive high frequency eddy current inspections to detect cracking 
around the attachment holes for the access panels in the lower skin of 
the wing, between ribs 13 and 22 (skin panel number 2, left and right 
sides); and repair, if necessary. The DGAC classified this service 
bulletin as mandatory and issued French airworthiness directive 97-083-
096(B), dated March 12, 1997, in order to assure the continued 
airworthiness of these airplanes in France.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 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 require accomplishment 
of the actions specified in the service bulletin described previously, 
except as discussed below.

Differences Between the Rule and the Service Information

    Operators should note that, although the previously described 
service bulletin specifies 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

    Currently, there are approximately 118 Airbus Model A320-111 
airplanes of U.S. registry. However, the FAA has determined that none 
of these U.S.-registered airplanes will be affected by this AD. 
Therefore, there is no future economic cost impact of this rule on U.S. 
operators.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 8 work hours per 
airplane to accomplish the required inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
this AD would be $480 per airplane, per inspection cycle.

The Direct Final Rule Procedure

    The FAA anticipates that this regulation will not result in adverse 
or negative comment and, therefore, is issuing it as a direct final 
rule. The requirements of this direct final rule address and unsafe 
condition identified by a foreign civil airworthiness authority and do 
not impose a significant burden on affected operators. In accordance 
with 14 CFR 11.17, unless a written adverse or negative comment, or a 
written notice of intent to submit an adverse or negative comment, is 
received within the comment period, the regulation will become 
effective on the date specified above. After the close of the comment 
period, the FAA will publish a document in the Federal Register 
indicating that no adverse or negative comments were received; at that 
time, the AD number will be specified, and the date on which the final 
rule will become effective will be confirmed. If the FAA does receive, 
within the comment period, a written adverse or negative comment, or 
written notice of intent to submit such a comment, a document 
withdrawing the direct final rule will be published in the Federal 
Register, and a notice of proposed rulemaking may be published with a 
new comment period.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and an 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.
    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 98-NM-22-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.

[[Page 13510]]

    The FAA has determined that this regulation is noncontroversial and 
unlikely to result in adverse or negative comments. For reasons 
discussed in the preamble, I certify that this regulation (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) 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 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:

Airbus: Amendment 39-10410. Docket 98-NM-22-AD.

    Applicability: Model A320-111 series airplanes, as identified in 
Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 
1997, including Appendix 1; 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 detect and correct cracking around the attachment holes for 
the access panels in the lower skin of the wing, between ribs 13 and 
22 (skin panel number 2, left and right sides), which could result 
in reduced structural integrity of the airplane, accomplish the 
following:
    (a) Prior to the accumulation of 20,000 total flight cycles, or 
within 60 days after the effective date of this AD, whichever occurs 
later: Perform a high frequency eddy current inspection to detect 
cracking around the attachment holes for the access panels in the 
lower skin of the wing, between ribs 13 and 22; in accordance with 
Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 
1997, including Appendix 1. Thereafter, repeat the inspection at 
intervals not to exceed 15,000 flight cycles.
    (b) If any crack is detected during any inspection required by 
this AD, and the applicable service bulletin specifies to contact 
the manufacturer for an appropriate action: Prior to further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate.
    (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. 
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.

    (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.
    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A320-57-1056, Revision 1, dated July 15, 1997, including 
Appendix 1. 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 directive 97-083-096(B), dated March 12, 1997.

    (f) This amendment becomes effective on June 18, 1998.

    Issued in Renton, Washington, on March 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6947 Filed 3-19-98; 8:45 am]
BILLING CODE 4910-13-U