[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
