[Federal Register Volume 63, Number 204 (Thursday, October 22, 1998)]
[Rules and Regulations]
[Pages 56542-56544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28159]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-29-AD; Amendment 39-10851; AD 98-22-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 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 
repetitive inspections to detect fatigue cracking of the lower surface 
panel on the wing center box; and repair, if necessary. This amendment 
also requires modification of the lower surface panel on the wing 
center box, which constitutes terminating action for the repetitive 
inspections. 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 the lower surface panel on the wing center box, 
which could result in reduced structural integrity of the airplane.

DATES: Effective November 27, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 27, 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

[[Page 56543]]

published in the Federal Register on August 26, 1998 (63 FR 45423). 
That action proposed to require repetitive inspections to detect 
fatigue cracking of the lower surface panel on the wing center box; and 
repair, if necessary. That action also proposed to require modification 
of the lower surface panel on the wing center box, which constitutes 
terminating action for the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    The commenters support the proposed rule.

Conclusion

    After careful review of the available data, including the comments 
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 60 airplanes of U.S. registry will be 
affected by this AD. It will take approximately 2 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 
the inspection required by this AD on U.S. operators is estimated to be 
$7,200, or $120 per airplane, per inspection cycle.
    It will take approximately 2 work hours per airplane to accomplish 
the required modification, at an average labor rate of $60 per work 
hour. There are no parts necessary to accomplish the modification. 
Based on these figures, the cost impact of the modification required by 
this AD on U.S. operators is estimated to be $7,200, or $120 per 
airplane.
    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.

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:

98-22-05  Airbus Industrie: Amendment 39-10851. Docket 98-NM-29-AD.

    Applicability: Model A320 series airplanes on which Airbus 
Modification 22418 (reference Airbus Service Bulletin A320-57-1043, 
Revision 02, dated May 14, 1997) has not been accomplished, 
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 (f) 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 lower surface panel on the 
wing center box, which could result in reduced structural integrity 
of the airplane, accomplish the following:
    (a) Except as provided by paragraph (e) of this AD: 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 fatigue cracking of 
the lower surface panel on the wing center box, in accordance with 
Airbus Service Bulletin A320-57-1082, Revision 01, dated December 
10, 1997. Repeat the eddy current inspection thereafter at intervals 
not to exceed 7,500 flight cycles until the actions required by 
paragraph (c) of this AD are accomplished.
    (b) Except as provided by paragraph (d) of this AD: If any 
cracking is detected during any inspection required by paragraph (a) 
of this AD, prior to further flight, repair in accordance with 
Airbus Service Bulletin A320-57-1082, Revision 01, dated December 
10, 1997. Accomplishment of the repair constitutes terminating 
action for the repetitive inspections for the repaired area only.
    (c) Prior to the accumulation of 25,000 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 
fatigue cracking of the lower surface panel on the wing center box, 
in accordance with Airbus Service Bulletin A320-57-1082, Revision 
01, dated December 10, 1997.
    (1) If no cracking is detected: Prior to further flight, modify 
the lower surface panel on the wing center box, in accordance with 
Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 
1997. Accomplishment of the modification constitutes terminating 
action for the requirements of this AD.
    (2) Except as provided by paragraph (d) of this AD, if any 
cracking is detected: Prior to further flight, repair in accordance 
with Airbus Service Bulletin A320-57-1082, Revision 01, dated 
December 10, 1997; and modify any uncracked area in accordance with 
Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 
1997. Accomplishment of the repair of cracked area(s) and 
modification of uncracked area(s) constitutes terminating action for 
the requirements of this AD.
    (d) If any cracking is detected during any inspection required 
by paragraph (b) or (c)(2) of this AD, and the applicable service 
bulletin specifies to contact Airbus for an 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).
    (e) The actions required by paragraph (a) of this AD are not 
required to be accomplished if the requirements of paragraph (c) of 
this AD are accomplished at the time specified in paragraph (a) of 
this AD.
    (f) 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

[[Page 56544]]

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.

    (g) 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.
    (h) Except as provided by paragraph (d) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A320-57-
1082, Revision 01, dated December 10, 1997, and Airbus Service 
Bulletin A320-57-1043, Revision 02, dated May 14, 1997, which 
contains the following list of effective pages:

------------------------------------------------------------------------
                                  Revision level
          Page Number             shown on page     Date shown on page
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1-6, 8, 13-14..................  02.............  May 14, 1997.
7, 9-12, 15....................  Original.......  Feb. 16, 1993.
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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 97-309-104(B), dated October 22, 1997.

    (i) This amendment becomes effective on November 27, 1998.

    Issued in Renton, Washington, on October 14, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-28159 Filed 10-21-98; 8:45 am]
BILLING CODE 4910-13-U