[Federal Register Volume 62, Number 125 (Monday, June 30, 1997)]
[Rules and Regulations]
[Pages 35072-35073]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-16854]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-182-AD; Amendment 39-10059; AD 97-14-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie 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 Industrie Model A300-600 series airplanes, 
that requires repetitive eddy current inspections to detect cracks of 
the outer skin of the fuselage at certain frames, and repair or 
reinforcement of the structure at the frames, if necessary. This 
amendment also requires eventual reinforcement of the structure at 
certain frames, which, when accomplished, terminates the repetitive 
inspections. This amendment is prompted by a report indicating that 
fatigue cracks were found in the area of certain frames. The actions 
specified by this AD are intended to prevent such fatigue cracking, 
which could reduce the structural integrity of the airframe and result 
in rapid decompression of the airplane.

DATES: Effective August 4, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 4, 1997.

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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; 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 Industrie Model 
A300-600 series airplanes was published in the Federal Register on 
March 26, 1997 (62 FR 14361). That action proposed to require 
repetitive eddy current inspections to detect cracks of the outer skin 
of the fuselage at frames 28A and 30A above stringer 30; and repair or 
reinforcement of the structure of the frames, if necessary. 
Additionally, that action proposed to require eventual reinforcement of 
the structure at frames 28 and 29, and frames 30 and 31, between 
stringers 29 and 30, which, when accomplished, terminates the 
repetitive inspections.
    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.
    The FAA has revised paragraph (a)(2) of this AD by adding the 
phrase ``prior to further flight'' to clarify the compliance time for 
the repair or reinforcement of any cracking found. This phrase was 
omitted inadvertently from the proposed rule.
    The FAA also has removed NOTE 1 of the proposal, which excluded 
certain airplanes from the applicability of this AD. The FAA considers 
it unnecessary to include this information in the final rule.

Conclusion

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

Cost Impact

    The FAA estimates that 34 Airbus Industrie Model A300-600 series 
airplanes of U.S. registry will be affected by this AD.
    The eddy current inspection that is required by this AD will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the required inspection on U.S. operators is estimated to be 
$2,040, or $60 per airplane, per inspection cycle.
    The reinforcement that is required by this AD will take 
approximately 93 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$7,200 per airplane. Based on these figures, the cost impact of the 
required modification on U.S. operators is estimated to be $434,520, or 
$12,780 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

[[Page 35073]]

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:

97-14-02  Airbus Industrie: Amendment 39-10059. Docket 96-NM-182-AD.

    Applicability: Model A300-600 series airplanes on which Airbus 
Modification 8683 was not accomplished during production, or on 
which Airbus Modification 8684 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 (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 fatigue cracking of the fuselage outer skin at frames 
28A and 30A, which could reduce the structural integrity of the 
airframe and result in rapid decompression of the airplane, 
accomplish the following:
    (a) Prior to the accumulation of 14,100 total flight cycles, or 
within 12 months after the effective date of the AD, whichever 
occurs later, conduct an eddy current inspection to detect cracking 
of the fuselage outer skin at frames 28A and 30A above stringer 30, 
in accordance with Airbus Service Bulletin A300-53-6045, dated March 
21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995.
    (1) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 4,500 flight cycles.
    (2) If any cracking is found that is within the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with paragraph 2.D. of the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as 
revised by Change Notice No. O.A., dated June 1, 1995; or reinforce 
the structure at frames 28 and 29, and at frames 30 and 31, between 
stringers 29 and 30, in accordance with Airbus Service Bulletin 
A300-53-6037, dated March 21, 1995.
    (i) If the repair is accomplished: After the repair, repeat the 
eddy current inspection thereafter at intervals not to exceed 4,500 
flight cycles.
    (ii) If the reinforcement is accomplished: Such reinforcement 
constitutes terminating action for the repetitive inspections 
required by this AD.
    (3) If any cracking is found that is outside the limits 
specified in the service bulletin, prior to further flight, 
reinforce the structure at frames 28 and 29, and at frames 30 and 
31, between stringers 29 and 30, in accordance with Airbus Service 
Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement 
constitutes terminating action for the repetitive inspections 
required by this AD.
    (b) Within 5 years after the effective date of this AD, 
reinforce the structure at frames 28 and 29, and at frames 30 and 
31, between stringers 29 and 30, in accordance with Airbus Service 
Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement 
constitutes terminating action for the repetitive inspections 
required by this AD.
    (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, 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.

    (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 A300-53-6045, dated March 21, 1995, as revised by Change 
Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin 
A300-53-6037, dated March 21, 1995. 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.
    (f) This amendment becomes effective on August 4, 1997.

    Issued in Renton, Washington, on June 23, 1997.
S.R. Miller,
Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-16854 Filed 6-27-97; 8:45 am]
BILLING CODE 4910-13-U