[Federal Register Volume 62, Number 66 (Monday, April 7, 1997)]
[Rules and Regulations]
[Pages 16473-16474]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8422]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-105-AD; Amendment 39-9988; AD 97-07-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 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 A320 series airplanes, that requires
modification of an area on the front spar of the wing center section by
installing shims and new fasteners to reinforce pressure floor
fittings. This amendment is prompted by a report from the manufacturer
indicating that full-scale fatigue testing on the test model revealed
fatigue cracking in this area. The actions specified by this AD are
intended to prevent fatigue cracking in this area, which can reduce the
structural integrity of fuselage frame 36 and the wing center section.
DATES: Effective May 12, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 12, 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 (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 certain Airbus Model A320 series
airplanes was published in the Federal Register on January 21, 1997 (62
FR 2982). That action proposed to require modification of an area on
the front spar of the wing center section by installing shims and new
fasteners to reinforce pressure floor fittings.
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 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 5 Airbus Model A320 series airplanes of U.S.
registry will be affected by this AD, that it will take approximately
13 work hours per airplane to accomplish the required actions, and that
the average labor rate is $60 per work hour. Required parts will cost
approximately $576 per airplane. Based on these figures, the cost
impact of the AD on U.S. operators is estimated to be $6,780, or $1,356
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:
[[Page 16474]]
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:
97-07-14 Airbus Industrie: Amendment 39-9988. Docket 96-NM-105-AD.
Applicability: Model A320 series airplanes as listed in Airbus
Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992;
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 (b) 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 in the rib flange of the front spar
side of the wing center section, and consequent reduced structural
integrity of fuselage frame 36 and the wing center section,
accomplish the following:
(a) Prior to the accumulation of 16,000 total landings, or
within 3 months after the effective date of this AD, whichever
occurs later, modify the rib flange on the front spar of the wing
center section by installing shims and new fasteners to reinforce
pressure floor fittings, in accordance with Airbus Service Bulletin
A320-57-1013, Revision 1, dated September 29, 1992.
Note 2: Modification of the rib flange accomplished prior to the
effective date of this AD in accordance with Airbus Service Bulletin
A320-57-1013, dated April 12, 1989, is considered acceptable for
compliance with the modification required by this AD.
(b) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) Special flight permits may be issued in accordance with
Secs. 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.
(d) The modification shall be done in accordance with Airbus
Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992,
which contains the following list of effective pages:
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Page No. Revision level shown on page Date shown on page
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1-3...................................... 1........................... September 29, 1992.
4-11..................................... Original.................... April 12, 1989.
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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.
(e) This amendment becomes effective on May 12, 1997.
Issued in Renton, Washington, on March 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-8422 Filed 4-4-97; 8:45 am]
BILLING CODE 4910-13-U
