[Federal Register Volume 63, Number 175 (Thursday, September 10, 1998)]
[Rules and Regulations]
[Pages 48421-48422]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-24062]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-159-AD; Amendment 39-10749; AD 98-19-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111, -211, and -231 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 series airplanes, that requires 
modification of certain fastener holes on the outer frames of the 
fuselage, and installation of new, improved fasteners. This amendment 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent fatigue cracking of 
certain fastener holes on the outer frames of the fuselage, which could 
result in reduced structural integrity of the airplane.

DATES: Effective October 15, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 15, 1998.

ADDRESSES: 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A320 series 
airplanes was published in the Federal Register on July 15, 1998 (63 FR 
38122). That action proposed to require modification of certain 
fastener holes on the outer frames of the fuselage, and installation of 
new, improved fasteners.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 9 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 6 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Required parts will cost approximately $390 
per airplane. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $6,750, or $750 per airplane.
    The cost impact figure discussed above is 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.

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.
    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:

98-19-07  Airbus Industrie: Amendment 39-10749. Docket 97-NM-159-AD.

    Applicability: Model A320-111, -211, and -231 series airplanes; 
on which Airbus Modification 20903 has not been installed; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (b) 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.


[[Page 48422]]


    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking of certain fastener holes on the 
outer frames of the fuselage, 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 4,000 flight cycles after the effective date of this AD, 
whichever occurs later, remove the existing fasteners located at 
fuselage frame 35 between the left- and right-hand stringers 30 and 
31, and perform a rotating probe inspection to detect fatigue 
cracking of the fastener holes, in accordance with Airbus Service 
Bulletin A320-53-1137, dated June 24, 1997.
    (1) If no cracking is detected, prior to further flight, modify 
the fastener holes and install new, improved fasteners, in 
accordance with the service bulletin.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate; or the 
Direction Generale de l'Aviation Civile (or its delegated agent).
    (b) 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.

    (c) 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.
    (d) Except as provided by paragraph (a)(2) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A320-53-1137, dated June 24, 1997. 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 98-154-113(B), dated April 8, 1998.

    (e) This amendment becomes effective on October 15, 1998.

    Issued in Renton, Washington on September 1, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-24062 Filed 9-9-98; 8:45 am]
BILLING CODE 4910-13-U