[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Rules and Regulations]
[Pages 40816-40817]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-116-AD; Amendment 39-10687; AD 98-16-11]
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 detailed visual inspections to 
detect cracks in the pylon thrust and sideload fitting of the wing, and 
replacement of any cracked pylon thrust and sideload fitting with a new 
fitting. 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 pylon thrust and sideload fitting of the wing, which 
could result in reduced structural integrity of the airplane.

DATES: Effective September 4, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 4, 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 certain Airbus Model A300, A310, 
and A300-600 series airplanes was published in the Federal Register on 
May 28, 1998 (63 FR 29153). That action proposed to require repetitive 
detailed visual inspections to detect cracks in the pylon thrust and 
sideload fitting of the wing, and replacement of any cracked pylon 
thrust and sideload fitting with a new fitting.

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 supports the proposed rule.

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 126 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 3 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 $22,680, or $180 
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

[[Page 40817]]

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:

98-16-11  Airbus Industrie: Amendment 39-10687. Docket 98-NM-116-AD.

    Applicability: Model A300 series airplanes, as listed in Airbus 
Service Bulletin A300-57-0232, Revision 01, dated January 12, 1998; 
Model A310 series airplanes, as listed in Airbus Service Bulletin 
A310-57-2075, Revision 01, dated January 12, 1998; and Model A300-
600 series airplanes, as listed in Airbus Service Bulletin A300-57-
6079, Revision 02, dated January 12, 1998; 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 cracks in the pylon thrust and sideload 
fitting of the wing, which could result in reduced structural 
integrity of the airplane, accomplish the following:
    (a) Prior to the accumulation of 2,800 total flight cycles, or 
within 18 months after the effective date of this AD, whichever 
occurs later, perform a detailed visual inspection to detect cracks 
in the pylon thrust and sideload fitting of the wing, in accordance 
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model 
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 
series airplanes); all dated January 12, 1998; as applicable. Repeat 
the detailed visual inspection thereafter at intervals not to exceed 
2,800 flight cycles.
    (b) If any crack is detected during any inspection required by 
paragraph (a), prior to further flight, replace the pylon thrust and 
sideload fitting with a new fitting in accordance with Airbus 
Service Bulletin A300-57-0232, Revision 01 (for Model A300 series 
airplanes); A310-57-2075, Revision 01 (for Model A310 series 
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series 
airplanes); all dated January 12, 1998; as applicable. Thereafter, 
continue the inspections in accordance with the requirements of 
paragraph (a) of 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, 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 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 inspections and replacement shall be done in accordance 
with Airbus Service Bulletin A300-57-0232, Revision 01, dated 
January 12, 1998; Airbus Service Bulletin A310-57-2075, Revision 01, 
dated January 12, 1998; or Airbus Service Bulletin A300-57-6079, 
Revision 02, dated January 12, 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 3: The subject of this AD is addressed in French 
airworthiness directive 97-358-232(B), dated November 19, 1997.

    (f) This amendment becomes effective on September 4, 1998.

    Issued in Renton, Washington, on July 24, 1998.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-20434 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U