[Federal Register Volume 62, Number 148 (Friday, August 1, 1997)]
[Rules and Regulations]
[Pages 41257-41259]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-20131]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-228-AD; Amendment 39-10097; AD 97-16-06]
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 all Airbus Model A300-600 series airplanes, that requires 
an inspection to detect cracks of certain attachment holes; and 
installation of a new fastener and follow-on inspections or repair, if 
necessary. This amendment is prompted by reports of fatigue cracking 
found on the forward fitting of frame 47 at the level of the last 
fastener of the external angle fitting. The actions specified by this 
AD are intended to prevent such fatigue cracking, which could result in 
reduced structural integrity of the airframe.

DATES: Effective September 5, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 5, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained

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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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 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 April 15, 1996 (61 
FR 16418). That action proposed to require a rotating probe inspection 
to detect cracks of the attachment holes H and I, and installation of a 
new fastener and follow-on inspections, if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    Both 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 35 Airbus Model A300-600 series airplanes of 
U.S. registry will be affected by this AD, that it will take 
approximately 37 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. The 
required kits for accomplishing the inspection will cost approximately 
$75 per airplane. Based on these figures, the cost impact of the AD on 
U.S. operators is estimated to be $80,325, or $2,295 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 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:

97-16-06  Airbus Industrie: Amendment 39-10097. Docket 95-NM-228-AD.

    Applicability: All Model A300-600 series 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 (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 on the forward fitting of frame 47 
at the level of the last fastener of the external angle fitting, 
which could result in reduced structural integrity of the airframe, 
accomplish the following:
    (a) Perform a rotating probe inspection to detect cracks of the 
attachment holes H and I in accordance with Airbus Service Bulletin 
A300-57-6049, dated September 9, 1994, at the applicable time 
specified in paragraph (a)(1) or (a)(2) of this AD.
    (1) For airplanes on which Airbus Modification 10454 (reference 
Airbus Service Bulletin A300-57-6050) has not been installed: 
Inspect prior to the accumulation of 13,800 total landings, or 
within 750 landings after the effective date of this AD.
    (2) For airplanes on which Airbus Modification 10454 (reference 
Airbus Service Bulletin A300-57-6050) or Airbus Modification 10155 
has been installed: Inspect prior to the accumulation of 18,700 
total landings, or within 750 landings after the effective date of 
this AD.
    (b) If no crack is found, prior to further flight, install a new 
fastener in accordance with Airbus Service Bulletin A300-57-6049, 
dated September 9, 1994. Repeat the rotating probe inspection 
thereafter at intervals not to exceed 5,600 landings.
    (c) If any crack in hole I is found to be greater than 0.196 
inches in length and/or depth, prior to further flight, repair it in 
accordance with a method approved by the
    Manager, Standardization Branch, ANM-113, FAA, Transport 
Airplane Directorate.
    (d) If any crack in hole H is found to be greater than .062 
inches in length, prior to further flight, repair it in accordance 
with a method approved by the Manager, Standardization Branch, ANM-
113.
    (e) If any crack in hole H or hole I is found to be less than or 
equal to the limits specified in paragraphs (c) and (d) of this AD, 
prior to further flight, repair it in accordance with Airbus Service 
Bulletin A300-57-6049, dated September 9, 1994.
    (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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (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

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a location where the requirements of this AD can be accomplished.
    (h) The inspection, installation, and certain repair shall be 
done in accordance with Airbus Service Bulletin A300-57-6049, dated 
September 9, 1994. 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.
    (i) This amendment becomes effective on September 5, 1997.

    Issued in Renton, Washington, on July 25, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-20131 Filed 7-31-97; 8:45 am]
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