[Federal Register Volume 65, Number 70 (Tuesday, April 11, 2000)]
[Rules and Regulations]
[Pages 19308-19310]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-8514]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-205-AD; Amendment 39-11661; AD 2000-07-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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 series airplanes, that requires 
modification of wing center box angle fittings at frame 47. 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 reduced structural 
integrity of the wing center box angle fittings at frame 47 due to 
fatigue cracking.

DATES: Effective May 16, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 16, 2000.

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

[[Page 19309]]

include an airworthiness directive (AD) that is applicable to certain 
Airbus Model A300 series airplanes was published in the Federal 
Register on January 27, 2000 (65 FR 4386). That action proposed to 
require modification of wing center box angle fittings at frame 47.

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 states that it is not affected by the proposal.

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 38 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 430 work hours per 
airplane to accomplish the required modification, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$8,840 per airplane. Based on these figures, the cost impact of the AD 
on U.S. operators is estimated to be $1,316,320, or $34,640 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 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 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:

2000-07-07 Airbus Industrie: Amendment 39-11661. Docket 99-NM-205-
AD.

    Applicability: Model A300 series airplanes, as listed in Airbus 
Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998; 
certificated in any category; except those on which Airbus Service 
Bulletin A300-53-0282 or Airbus Service Bulletin A300-53-0291 has 
been accomplished.

    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 reduced structural integrity of the wing center box 
angle fittings at frame (FR) 47, accomplish the following:
    (a) Prior to the accumulation of the applicable threshold 
specified in the ``MANDATORY TH'' column of the table in paragraph 
1.B.(4) of the service bulletin, or within 6,500 flight cycles after 
the effective date of this AD, whichever occurs later: Except as 
required by paragraph (b) of this AD, modify the wing center box 
angle fittings at FR 47 (including removing certain sealant and 
fasteners, performing rotating probe inspections to detect cracking, 
cold working certain fastener holes, installing new fasteners and 
sealant, and repairing damage), in accordance with Airbus Service 
Bulletin A300-53-0298, Revision 03, dated November 26, 1998.

    Note 2: Operators should note that the area required to be 
modified by paragraph (a) of this AD remains subject to the 
requirements of AD 96-13-11, amendment 39-9679, after modification.

    (b) Where Airbus Service Bulletin A300-53-0298, Revision 03, 
dated November 26, 1998, specifies that Airbus be contacted for 
repair instructions for certain damage conditions, this AD requires 
that such damage conditions be repaired prior to further flight 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 (DGAC) (or its 
delegated agent). 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, 
Transport Airplane Directorate. 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 3: 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 
modification shall be done in accordance with Airbus Service 
Bulletin A300-53-0298, Revision 03, dated November 26, 1998, which 
contains the following list of effective pages:

[[Page 19310]]



------------------------------------------------------------------------
                                    Revision level
           Page number               shown on page    Date shown on page
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1-21, 32-40, 42-46, 67, 68, 71-   03................  November 26, 1998.
 74, 93, 94, 103-110, 151, 157-
 161, 205-214.
22-31, 41, 47-55, 57-66, 69, 70,  Original..........  October 14, 1993.
 75-92, 95-102, 152-156, 163-
 204, 215.
56, 102A, 102B, 111-150.........  1.................  March 17, 1994.
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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 4: The subject of this AD is addressed in French 
airworthiness directive 1999-076-267(B), dated February 24, 1999.

    (f) This amendment becomes effective on May 16, 2000.

    Issued in Renton, Washington, on March 31, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8514 Filed 4-10-00; 8:45 am]
BILLING CODE 4910-13-U