[Federal Register Volume 65, Number 54 (Monday, March 20, 2000)]
[Rules and Regulations]
[Pages 14853-14854]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6159]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-211-AD; Amendment 39-11628; AD 2000-05-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and 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, A310, and A300-600 series 
airplanes, that requires repetitive eddy current inspections to detect 
cracking on the door edge frames of the fuselage bulk cargo 
compartment, and repair, if necessary. 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 detect and correct cracks in the door edge frames of the 
fuselage bulk cargo compartment, which could result in reduced 
structural integrity of the airframe.

DATES: Effective April 24, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 24, 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 include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A300, A310, 
and A300-600 series airplanes was published in the Federal Register on 
January 4, 2000 (65 FR 254). That action proposed to require repetitive 
eddy current inspections to detect cracking on the door edge frames of 
the fuselage bulk cargo compartment, and repair, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Explanation of Changes Made to the Final Rule

    Since the issuance of the proposed rule, the FAA has reviewed and 
approved Revision 01 of Airbus Service Bulletins A310-53-2106, 
including Appendix 01; and A300-53-6114, including Appendix 01; both 
dated July 28, 1998. These revisions are essentially identical to the 
original issues, which were cited in the proposed AD as the appropriate 
source of service information for accomplishment of the specified 
actions. This final rule has been revised to include these revisions as 
additional sources of service information.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the changes described previously. The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Interim Action

    This is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the cracking, and 
eventually to develop final action to address the unsafe condition. 
Once final action has been identified, the FAA may consider further 
rulemaking.

Cost Impact

    The FAA estimates that 126 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $15,120, or $120 
per airplane, per inspection cycle.
    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

[[Page 14854]]

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:

2000-05-18 Airbus Industrie: Amendment 39-11628. Docket 98-NM-211-
AD.
    Applicability: Model A300 series airplanes on which Airbus 
Modification 2140 (reference Airbus Service Bulletin A300-53-109) 
has been accomplished; and Model A310 and A300-600 series airplanes, 
except those airplanes on which Airbus Modification 5438 was 
accomplished during production; 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 (d) 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 cracks in the door edge frames of the bulk 
cargo compartment, which could result in reduced structural 
integrity of the airframe, accomplish the following:

Repetitive Inspections

    (a) Perform an eddy current inspection to detect cracking in the 
inner and outer flanges on the door edge frames of the fuselage bulk 
cargo compartment, in accordance with Airbus Service Bulletins A300-
53-0339, Revision 01, including Appendix 01, dated July 28, 1998 
(for Model A300 series airplanes); A310-53-2106, including Appendix 
01, dated October 2, 1997; or A310-53-2106, Revision 01, including 
Appendix 01, dated July 28, 1998 (for Model A310 series airplanes); 
A300-53-6114, including Appendix 01, dated October 2, 1997; or A300-
53-6114, Revision 01, including Appendix 01, dated July 28, 1998 
(for Model A300-600 series airplanes); as applicable; at the 
applicable time specified in paragraph (a)(1) or (a)(2) of this AD. 
Thereafter, repeat the inspection at intervals not to exceed 5 
years.
    (1) For airplanes with less than 15 years since date of 
manufacture as of the effective date of this AD: Inspect within 10 
years since date of manufacture, or within 12 months after the 
effective date of this AD, whichever occurs later.
    (2) For airplanes with 15 or more years since date of 
manufacture as of the effective date of this AD: Inspect within 6 
months after the effective date of this AD.

    Note 2: For Model A300 series airplanes, accomplishment of an 
eddy current inspection prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-53-0339, dated October 
2, 1997, is considered acceptable for compliance with the initial 
eddy current inspection required by paragraph (a) of this AD.

Corrective Actions

    (b) If any crack is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair the door 
edge frame in accordance with Airbus Service Bulletins A300-53-0339, 
Revision 01, including Appendix 01, dated July 28, 1998 (for Model 
A300 series airplanes); 310-53-2106, including Appendix 01, dated 
October 2, 1997; or A310-53-2106, Revision 01, including Appendix 
01, dated July 28, 1998, (for Model A310 series airplanes); A300-53-
6114, including Appendix 01, dated October 2, 1997; or A300-53-6114, 
Revision 01, including Appendix 01, dated July 28, 1998 (for Model 
A300-600 series airplanes); as applicable. Complete replacement of a 
door edge frame with a new door frame in accordance with the service 
bulletin constitutes terminating action for the repetitive 
inspections required by this AD for that door frame only.

Report Requirements

    (c) Submit a report of the inspection results (both positive and 
negative findings) to Airbus Industrie, Customer Services 
Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, at the applicable time specified in paragraph (e)(1) or 
(e)(2) of this AD. Information collection requirements contained in 
this regulation have been approved by the Office of Management and 
Budget (OMB) under the provisions of the Paperwork Reduction Act of 
1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control 
Number 2120-0056.
    (1) For airplanes on which any inspection is accomplished after 
the effective date of this AD: Submit the report within 30 days 
after performing any inspection required by paragraph (a) or (b) of 
this AD.
    (2) For airplanes on which the inspection has been accomplished 
prior to the effective date of this AD: Submit the report within 10 
days after the effective date of this AD.

Alternative Methods of Compliance

    (d) 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

    (e) 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

    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A300-53-0339, Revision 01, including Appendix 01, dated 
July 28, 1998; Airbus Service Bulletin A310-53-2106, including 
Appendix 01, dated October 2, 1997; Airbus Service Bulletin A310-53-
2106, Revision 01, including Appendix 01, dated July 28, 1998; 
Airbus Service Bulletin A300-53-6114, including Appendix 01, dated 
October 2, 1997; or Airbus Service Bulletin A300-53-6114, Revision 
01, including Appendix 01, dated July 28, 1998; as applicable. 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 98-123-245(B), dated March 11, 1998.

    (g) This amendment becomes effective on April 24, 2000.

    Issued in Renton, Washington, on March 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-6159 Filed 3-17-00; 8:45 am]
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