[Federal Register Volume 63, Number 204 (Thursday, October 22, 1998)]
[Rules and Regulations]
[Pages 56542-56544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28159]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-29-AD; Amendment 39-10851; AD 98-22-05]
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
repetitive inspections to detect fatigue cracking of the lower surface
panel on the wing center box; and repair, if necessary. This amendment
also requires modification of the lower surface panel on the wing
center box, which constitutes terminating action for the repetitive
inspections. 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 prevent
fatigue cracking of the lower surface panel on the wing center box,
which could result in reduced structural integrity of the airplane.
DATES: Effective November 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 27, 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 A320 series
airplanes was
[[Page 56543]]
published in the Federal Register on August 26, 1998 (63 FR 45423).
That action proposed to require repetitive inspections to detect
fatigue cracking of the lower surface panel on the wing center box; and
repair, if necessary. That action also proposed to require modification
of the lower surface panel on the wing center box, which constitutes
terminating action for the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
The 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 60 airplanes of U.S. registry will be
affected by this AD. It will take approximately 2 work hours per
airplane to accomplish the required inspection, at an average labor
rate of $60 per work hour. Based on these figures, the cost impact of
the inspection required by this AD on U.S. operators is estimated to be
$7,200, or $120 per airplane, per inspection cycle.
It will take approximately 2 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. There are no parts necessary to accomplish the modification.
Based on these figures, the cost impact of the modification required by
this AD on U.S. operators is estimated to be $7,200, or $120 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 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:
98-22-05 Airbus Industrie: Amendment 39-10851. Docket 98-NM-29-AD.
Applicability: Model A320 series airplanes on which Airbus
Modification 22418 (reference Airbus Service Bulletin A320-57-1043,
Revision 02, dated May 14, 1997) has not been accomplished,
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 of the lower surface panel on the
wing center box, which could result in reduced structural integrity
of the airplane, accomplish the following:
(a) Except as provided by paragraph (e) of this AD: Prior to the
accumulation of 20,000 total flight cycles, or within 60 days after
the effective date of this AD, whichever occurs later, perform a
high frequency eddy current inspection to detect fatigue cracking of
the lower surface panel on the wing center box, in accordance with
Airbus Service Bulletin A320-57-1082, Revision 01, dated December
10, 1997. Repeat the eddy current inspection thereafter at intervals
not to exceed 7,500 flight cycles until the actions required by
paragraph (c) of this AD are accomplished.
(b) Except as provided by paragraph (d) of this AD: If any
cracking is detected during any inspection required by paragraph (a)
of this AD, prior to further flight, repair in accordance with
Airbus Service Bulletin A320-57-1082, Revision 01, dated December
10, 1997. Accomplishment of the repair constitutes terminating
action for the repetitive inspections for the repaired area only.
(c) Prior to the accumulation of 25,000 total flight cycles, or
within 60 days after the effective date of this AD, whichever occurs
later: Perform a high frequency eddy current inspection to detect
fatigue cracking of the lower surface panel on the wing center box,
in accordance with Airbus Service Bulletin A320-57-1082, Revision
01, dated December 10, 1997.
(1) If no cracking is detected: Prior to further flight, modify
the lower surface panel on the wing center box, in accordance with
Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14,
1997. Accomplishment of the modification constitutes terminating
action for the requirements of this AD.
(2) Except as provided by paragraph (d) of this AD, if any
cracking is detected: Prior to further flight, repair in accordance
with Airbus Service Bulletin A320-57-1082, Revision 01, dated
December 10, 1997; and modify any uncracked area in accordance with
Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14,
1997. Accomplishment of the repair of cracked area(s) and
modification of uncracked area(s) constitutes terminating action for
the requirements of this AD.
(d) If any cracking is detected during any inspection required
by paragraph (b) or (c)(2) of this AD, and the applicable service
bulletin specifies to contact Airbus for an appropriate action:
Prior to further flight, repair in accordance with a method approved
by either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Direction Generale de l'Aviation Civile
(or its delegated agent).
(e) The actions required by paragraph (a) of this AD are not
required to be accomplished if the requirements of paragraph (c) of
this AD are accomplished at the time specified in paragraph (a) of
this AD.
(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, International Branch, ANM-116.
Operators
[[Page 56544]]
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.
(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 a location where
the requirements of this AD can be accomplished.
(h) Except as provided by paragraph (d) of this AD, the actions
shall be done in accordance with Airbus Service Bulletin A320-57-
1082, Revision 01, dated December 10, 1997, and Airbus Service
Bulletin A320-57-1043, Revision 02, dated May 14, 1997, which
contains the following list of effective pages:
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Revision level
Page Number shown on page Date shown on page
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1-6, 8, 13-14.................. 02............. May 14, 1997.
7, 9-12, 15.................... Original....... Feb. 16, 1993.
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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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 97-309-104(B), dated October 22, 1997.
(i) This amendment becomes effective on November 27, 1998.
Issued in Renton, Washington, on October 14, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-28159 Filed 10-21-98; 8:45 am]
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