[Federal Register: July 27, 2004 (Volume 69, Number 143)]
[Rules and Regulations]
[Page 44592-44594]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27jy04-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-279-AD; Amendment 39-13741; AD 2004-15-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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 A310 series airplanes, that requires
repetitive inspections for fatigue cracking of the area around the
fasteners of the landing plate of the aileron access doors of the
bottom skin panel of the wings, and related corrective action. This
amendment also provides for an optional terminating action, which ends
the repetitive inspections. This action is necessary to prevent fatigue
cracking of the area around the fasteners of the landing plate of the
aileron access doors and the bottom skin panel of the wings, which
could result in reduced structural integrity of the wings. This action
is intended to address the identified unsafe condition.
DATES: Effective August 31, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 31, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 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 National Archives
and Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, 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
[[Page 44593]]
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A310 series
airplanes was published in the Federal Register on May 19, 2004 (69 FR
28867). That action proposed to require repetitive inspections for
fatigue cracking of the area around the fasteners of the landing plate
of the aileron access doors of the bottom skin panel of the wings, and
related corrective action. That action also provided for an optional
terminating action, which would end the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
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 46 airplanes of U.S. registry will be
affected by this AD, that it will take about 2 work hours per airplane
to accomplish the required actions, and that the average labor rate is
$65 per work hour. Based on these figures, the cost impact of the AD on
U.S. operators is estimated to be $5,980, or $130 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. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-15-07 Airbus: Amendment 39-13741. Docket 2003-NM-279-AD.
Applicability: Model A310 series airplanes, certificated in any
category; on which Airbus Modification 12525 has not been done
during production.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the area around the fasteners of
the landing plate of the aileron access doors and the bottom skin
panel of the wings, which could result in reduced structural
integrity of the wings, accomplish the following:
Repetitive Inspections
(a) For airplanes on which Airbus Modification 5106 (Airbus
Service Bulletin A310-57-2004, Revision 2, dated March 5, 1990) has
not been done as of the effective date of this AD: Within 2,000
flight cycles after the effective date of this AD, or within 3,000
flight cycles after the last inspection done per paragraph (k) of AD
98-26-01, amendment 39-10942 (63 FR 69179, December 16, 1998),
whichever is first; do a high frequency eddy current (HFEC)
inspection for cracking of the area around the fasteners of the
landing plate of the wing bottom skin panel No. 2 of the left and
right wings. Do the inspection per the Accomplishment Instructions
of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. If no
cracking is found, repeat the inspection thereafter at intervals not
to exceed 1,900 flight cycles, until accomplishment of the
terminating action specified in paragraph (d) of this AD.
(b) For airplanes on which Airbus Modification 5106 has been
done as of the effective date of this AD: Do the HFEC inspection
required by paragraph (a) of this AD at the applicable time
specified in paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this AD.
If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 1,900 flight cycles, until accomplishment of
the terminating action specified in paragraph (d) of this AD.
(1) For airplanes that have accumulated fewer than 17,000 total
flight cycles since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness, whichever is first, as of the
effective date of this AD: Inspect prior to the accumulation of
18,000 total flight cycles.
(2) For airplanes that have accumulated 17,000 or more total
flight cycles, but fewer than 19,001 total flight cycles since the
date of issuance of the original Airworthiness Certificate or the
date of issuance of the original Export Certificate of
Airworthiness, whichever is first, as of the effective date of this
AD: Inspect within 2,000 flight cycles after the effective date of
this AD.
(3) For airplanes that have accumulated 19,001 or more total
flight cycles, but fewer than 21,001 total flight cycles since the
date of issuance of the original Airworthiness Certificate or the
date of issuance of the original Export Certificate of
Airworthiness, whichever is first, as of the effective date of this
AD: Inspect with 1,200 flight cycles after the effective date of
this AD.
(4) For airplanes that have accumulated 21,001 or more total
flight cycles since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness, whichever is first, as of the
effective date of this AD: Inspect within 500 flight cycles after
the effective date of this AD.
Corrective Action
(c) If any cracking is found during any inspection required by
paragraph (a) or (b) of this AD: Before further flight, do the
actions required by either paragraph (c)(1) or (c)(2) of this AD.
(1) Do a permanent repair of the area by doing the applicable
corrective actions per the Accomplishment Instruction of Airbus
Service Bulletin A310-57-2082, dated June 11, 2002. Accomplishment
of the permanent repair terminates the repetitive inspections
required by this AD for the repaired area only.
(2) Do the terminating action specified in paragraph (d) of this
AD.
Optional Terminating Action
(d) Modification of the landing plate of the aileron access
doors of the wing bottom skin panel No. 2 of the left and right
wings by doing all the actions, per the
[[Page 44594]]
Accomplishment Instructions of Airbus Service Bulletin A310-57-2081,
dated June 11, 2002, terminates the requirements of this AD. Where
the service bulletin specifies contacting the manufacturer for
disposition of certain repair conditions that may be associated with
the modification procedure, this AD requires that the repair be done
per 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.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions shall be
done in accordance with Airbus Service Bulletin A310-57-2082, dated
June 11, 2002. The optional terminating action, if accomplished,
shall be done in accordance with Airbus Service Bulletin A310-57-
2081, dated June 11, 2002. 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, 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 National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go
to: http://www. archives. gov/ federal-- register/ code-- of--
federal-- regulations/ibr--locations.html.
Note 1: The subject of this AD is addressed in French
airworthiness directive 2003-242(B), dated June 25, 2003.
Effective Date
(g) This amendment becomes effective on August 31, 2004.
Issued in Renton, Washington, on July 9, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-16675 Filed 7-26-04; 8:45 am]
BILLING CODE 4910-13-P