[Federal Register Volume 63, Number 237 (Thursday, December 10, 1998)]
[Rules and Regulations]
[Pages 68167-68169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32623]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-153-AD; Amendment 39-10933; AD 98-25-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 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 A300-600 series airplanes, that 
requires repetitive inspections to detect cracks in the angle fitting 
at frame 40 of the center wing box, and corrective actions, if 
necessary; and eventual modification of that angle fitting, which 
terminates 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 cracks in the center wing box angle fitting, which 
could result in the failure of the center wing box at frame 40, and 
consequent reduced structural integrity of the airplane.

DATES: Effective January 14, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 14, 1999.


[[Page 68168]]


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 A300-600 
series airplanes was published as a supplemental notice of proposed 
rulemaking (NPRM) in the Federal Register on October 14, 1998 (63 FR 
55063). That action proposed to require repetitive inspections to 
detect cracks in the angle fitting at frame 40 of the center wing box, 
and corrective actions, if necessary; and eventual modification of that 
angle fitting, which would terminate 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 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 54 Model A300-600 series airplanes of U.S. 
registry will be affected by this AD.
    It will take approximately 36 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 $116,640, or $2,160 per 
airplane, per inspection cycle.
    It will take approximately 754 work hours per airplane to 
accomplish the required modification, at an average labor rate of $60 
per work hour. Required parts will cost approximately $11,605 per 
airplane. Based on these figures, the cost impact of the modification 
required by this AD on U.S. operators is estimated to be $3,069,630, or 
$56,845 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:

98-25-07 Airbus: Amendment 39-10933. Docket 97-NM-153-AD.

    Applicability: Model A300-600 series airplanes on which Airbus 
Modification 10453 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 (e) 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 cracks in the center wing box angle fitting, which 
could result in the failure of the center wing box at frame 40, and 
consequent reduced structural integrity of the airplane, accomplish 
the following:
    (a) Prior to the accumulation of the threshold specified in 
Table 1 of this AD, as applicable, or within 1,500 flight cycles 
after the effective date of this AD, whichever occurs later: Perform 
a detailed visual, eddy current, or liquid penetrant inspection to 
detect cracking in the angle fitting of frame 40 (both left and 
right), with the nut removed, in accordance with Airbus Service 
Bulletin A300-57-6052, Revision 1, dated July 22, 1996. Thereafter, 
repeat the inspections at the interval specified in Table 1 of this 
AD, as applicable, until the actions required by paragraph (c) of 
this AD have been accomplished.

[[Page 68169]]



                                                     Table 1
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                                                                                                   Eddy current/
                                                                                      Visual          liquid
                                                                     Threshold      inspection       penetrant
      Average flight time (AFT): flight hours/flight cycles           (flight        interval       inspection
                                                                      cycles)         (flight        interval
                                                                                      cycles)         (flight
                                                                                                      cycles)
----------------------------------------------------------------------------------------------------------------
2.10-2.49.......................................................           5,900           4,700           5,300
2.50-2.99.......................................................           5,600           4,400           4,900
3.00-3.49.......................................................           5,200           4,100           4,600
3.50-3.99.......................................................           4,800           3,800           4,200
4.00-4.49.......................................................           4,400           3,500           3,900
4.50-4.99.......................................................           4,000           3,200           3,500
5.00-5.49.......................................................           3,600           2,800           3,200
5.50-5.99.......................................................           3,200           2,500           2,800
6.00-6.50.......................................................           2,800           2,200           2,500
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    (b) Except as provided by paragraph (d) of this AD, if any crack 
is found during an inspection required by paragraph (a) of this AD, 
prior to further flight, accomplish follow-on corrective actions in 
accordance with the procedures specified in Airbus Service Bulletin 
A300-57-6052, Revision 1, dated July 22, 1996.
    (c) Within 4 years after the effective date of this AD, modify 
the angle fitting at frame 40 (both left and right) in accordance 
with Airbus Service Bulletin A300-57-6053, Revision 1, dated October 
31, 1995. Accomplishment of the modification constitutes terminating 
action for the repetitive inspections required by paragraph (a) of 
this AD.
    (d) If any crack is found during an inspection required by 
paragraph (a) of 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.
    (e) 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.

    (f) 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.
    (g) Except as provided by paragraph (d) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A300-57-
6052, Revision 1, dated July 22, 1996; and Airbus Service Bulletin 
A300-57-6053, Revision 1, dated October 31, 1995, which contains the 
following list of effective pages:

----------------------------------------------------------------------------------------------------------------
                                                  Revision level shown
                    Page No.                             on page                    Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 7-9, 11-15, 19-24, 35, 36, 41, 42, 45-47....  1                       October 31, 1995.
2-6, 10, 16-18, 25-34, 37-40, 43, 44...........  Original                February 21, 1995.
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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 (CN) 95-111-181(B) R1, dated October 23, 
1996.

    (h) This amendment becomes effective on January 14, 1999.

    Issued in Renton, Washington, on December 2, 1998.
John W. McGraw,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-32623 Filed 12-9-98; 8:45 am]
BILLING CODE 4910-13-P