Airworthiness Directives; Airbus Industrie Model A300-600 Series Airplanes

[Federal Register Volume 63, Number 185 (Thursday, September 24, 1998)]
[Rules and Regulations]
[Pages 50981-50983]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25354]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-82-AD; Amendment 39-10793; AD 98-20-27]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie Model A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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[[Page 50982]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300-600 series airplanes, that requires 
repetitive inspections to detect fatigue cracking of the wing top skin 
at the front spar joint; and a follow-on eddy current inspection 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 fatigue cracking of the wing top skin at the 
front spar joint, which could result in reduced structural integrity of 
the airplane.

DATES: Effective October 29, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 29, 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 all Airbus Model A300-600 series 
airplanes was published in the Federal Register on May 12, 1998 (63 FR 
26109). That action proposed to require repetitive inspections to 
detect fatigue cracking of the wing top skin at the front spar joint; 
and a follow-on eddy current inspection and repair, if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter expresses no objection to the proposed rule.

Request To Allow Flight With Known Cracks

    One commenter recommends that the proposed AD be revised to allow 
continued operation of an unrepaired airplane following detection of 
cracks, utilizing the allowable damage limits and temporary repairs 
described in Airbus Service Bulletin A300-57-6045. The commenter 
expresses confidence that allowing continued flight within the 
allowable crack limits and with the temporary repairs specified in the 
service bulletin will provide the necessary level of safety. The 
commenter further states that the manufacturer has not identified a 
permanent repair for the area, nor has a preventive modification been 
identified that would allow termination of the inspections required by 
this proposed AD. Additionally, the commenter notes that the area where 
the cracks may occur would require an extensive internal repair that 
has not been developed at this time. If such cracking occurs, an 
airplane could be grounded for a long time period while a repair is 
developed, analyzed, and approved.
    The FAA does not concur. It is the FAA's policy to require repair 
of known cracks prior to further flight (except in certain cases of 
unusual need). This policy is based on the fact that such damaged 
airplanes do not conform to the FAA certificated type design, and 
therefore, are not airworthy until a properly approved repair is 
incorporated. Although the referenced service bulletin specifies 
temporary repairs for certain crack findings, it does not provide such 
repairs for cracking outside certain limits. For those cases, the 
service bulletin specifies that, depending upon crack length, operators 
should either contact the manufacturer for appropriate repairs or 
accomplish repetitive visual inspections at specified intervals. 
Therefore, the FAA has determined that, due to the safety implications 
and consequences associated with cracking of the wing top skin at the 
front spar joint, any subject area that is found to be cracked must be 
addressed, prior to further flight, in accordance with a method 
approved by the FAA.

Later Revision of Service Bulletin

    One commenter has provided a copy of Airbus Service Bulletin A300-
57-6045, Revision 02, dated April 21, 1998, including Appendix 1, 
Revision 02, dated April 21, 1998, but makes no specific request in 
regard to this revision. Airbus Service Bulletin A300-57-6045, Revision 
1, dated August 3, 1994, including Appendix 1, Revision 1, dated August 
3, 1994, was cited in the proposed AD as the appropriate source of 
service information for accomplishment of the actions required by this 
AD. The FAA has reviewed Revision 02 of the service bulletin and has 
determined that it contains no substantive differences from Revision 1. 
Therefore, the final rule has been revised to add Revision 02 as an 
appropriate source of service information.

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 with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 54 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 inspection required by this AD on U.S. operators is 
estimated to be $6,480, 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 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.

[[Page 50983]]

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:

98-20-27  Airbus Industrie: Amendment 39-10793. Docket 98-NM-82-AD.

    Applicability: All Model A300-600 airplanes, 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 (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 detect and correct fatigue cracking of the wing top skin at 
the front spar joint, which could result in reduced structural 
integrity of the airplane, accomplish the following:
    (a) Prior to the accumulation of 22,000 total flight cycles, or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later, perform a detailed visual inspection to 
detect fatigue cracking of the wing top skin at the front spar 
joint, in accordance with Airbus Service Bulletin A300-57-6045, 
Revision 1, dated August 3, 1994, including Appendix 1, Revision 1, 
dated August 3, 1994; or Airbus Service Bulletin A300-57-6045, 
Revision 02, dated April 21, 1998, including Appendix 1, Revision 
02, dated April 21, 1998. Repeat the detailed visual inspection 
thereafter at intervals not to exceed 8,000 flight cycles.
    (b) If any cracking is suspected or detected during any 
inspection required by paragraph (a) of this AD, prior to further 
flight, perform an eddy current inspection to confirm the findings 
of the visual inspection, in accordance with Airbus Service Bulletin 
A300-57-6045, Revision 1, dated August 3, 1994, including Appendix 
1, Revision 1, dated August 3, 1994; or Airbus Service Bulletin 
A300-57-6045, Revision 02, dated April 21, 1998, including Appendix 
1, Revision 02, dated April 21, 1998. If any cracking is detected 
during any eddy current inspection, 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).
    (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. 
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.

    (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.
    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including 
Appendix 1, Revision 1, dated August 3, 1994; or Airbus Service 
Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including 
Appendix 1, Revision 02, dated April 21, 1998. Revision 1 of Airbus 
Service Bulletin A300-57-6045 contains the following list of 
effective pages:

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                                  Revision level
           Page No.               shown on page      Date shown on page
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1-10..........................  1................  August 3, 1994.
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                               Appendix 1
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1-2...........................  1................  August 3, 1994.
3-6...........................  Original.........  March 18, 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 97-374-238(B), dated December 3, 1997.

    (f) This amendment becomes effective on October 29, 1998.

    Issued in Renton, Washington, on September 16, 1998.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25354 Filed 9-23-98; 8:45 am]
BILLING CODE 4910-13-U

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