[Federal Register Volume 69, Number 131 (Friday, July 9, 2004)]
[Rules and Regulations]
[Pages 41401-41403]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15373]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-175-AD; Amendment 39-13715; AD 2004-14-06]
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 supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A310 series airplanes, that 
currently requires repetitive inspections of the fuselage skin to 
detect corrosion or fatigue cracking around and under the chafing 
plates of the wing root; and corrective actions, if necessary. That AD 
also provides an optional terminating action for the repetitive 
inspections. This amendment reinstates repetitive inspections in 
certain areas where corrosion was detected and reworked as required by 
the existing AD. The actions specified by this AD are intended to 
detect and correct fatigue cracks and corrosion around and under the 
chafing plates of the wing root, which could result in reduced 
structural integrity of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective August 13, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 13, 2004.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of June 3, 1998 (63 FR 23377, April 29, 1998).

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: Anthony Jopling, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2190; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-09-20, 
amendment 39-10501 (63 FR 23377, April 29, 1998), which is applicable 
to certain Airbus Model A310 series airplanes, was published in the 
Federal Register on December 18, 2003, (68 FR 70479). The action 
proposed to continue require reinstating repetitive inspections in 
certain areas where corrosion was detected and reworked as required by 
the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received from a single commenter.

Request to Reference Revised Service Information

    The commenter states that Airbus has issued Revision 05 to Service 
Bulletin A310-53-2069, dated November 12, 2002, and requests that this 
revision be included in the proposed AD as an acceptable source of 
service information. The commenter notes that Revision 05 of the 
service bulletin includes a revised repair drawing and, for certain 
airplanes, deletes an inspection at frame 39/stringer 35.
    The FAA concurs with the intent of the commenter's request to 
include Revision 05 of the service bulletin as an appropriate source of 
service information. However, upon review of Revisions 04 and 05 of the 
service bulletin, it appears that the repair drawing was revised in 
Revision 04, and that the manufacturer did not remove the revision 
marks when Revision 05 of the service bulletin was issued. We have 
determined that Revision 05 of Airbus Service Bulletin A310-53-2069 
adds no new requirements. We have revised paragraphs (a), (b), and (d) 
of this final rule to reference Airbus Service Bulletin A310-53-2069, 
Revision 05, dated November 12, 2002; and Revision 04, dated November 
8, 2000; as additional appropriate sources of service information.

Conclusion

    After careful review of the available data, including the comment 
noted above, we have determined that air safety and the public interest 
require the adoption of the rule with the change previously described. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Cost Impact

    There are approximately 46 airplanes of U.S. registry that will be 
affected by this AD. This AD adds no new requirements. It requires 
continuation of repetitive inspections for airplanes where corrosion 
was detected and reworked at frame 39, stringer 35. The current costs 
associated with AD 98-09-20 are reiterated in their entirety as follows 
for the convenience of affected operators:
    The actions that are currently required by AD 98-09-20 take 
approximately 68 work hours per airplane to accomplish, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of the previously required actions on U.S. operators is 
estimated to be $4,420 per airplane, per inspection cycle.

[[Page 41402]]

    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 removing amendment 39-10501 (63 FR 
23377, April 29, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-13715, to read as follows:

2004-14-06 Airbus: Amendment 39-13715. Docket 2002-NM-175-AD. 
Supersedes AD 98-09-20, Amendment 39-10501.

    Applicability: Model A310 series airplanes on which Airbus 
Modifications 8888 and 8889 have not been accomplished, certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking and corrosion around and 
under chafing plates of the wing root between fuselage frame 36 and 
frame 39, which could result in reduced structural integrity of the 
airplane, accomplish the following:

Restatement of Requirements of AD 98-09-20

Repetitive Inspections and Corrective Actions

    (a) Except as provided by paragraph (b) of this AD: Within 4 
years since date of manufacture, or within 12 months after June 3, 
1998 (the effective date of AD 98-09-20, amendment 39-10501), 
whichever occurs later, perform an inspection to detect 
discrepancies around and under the chafing plates of the wing root, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-53-2069, Revision 05, dated November 12, 2002; 
Revision 04, dated November 8, 2000; Revision 03, dated October 28, 
1997; Revision 2, dated September 23, 1996; or Revision 1, dated 
September 19, 1995. If any discrepancy is found, prior to further 
flight, accomplish follow-on corrective actions (i.e., removal of 
corrosion, corrosion protection, high frequency eddy current 
inspection, x-ray inspection), as applicable, in accordance with the 
applicable service bulletin. Repeat the inspections thereafter at 
the intervals specified in the applicable service bulletin. After 
the effective date of this AD, repeat the inspections thereafter at 
the intervals specified in Revision 04 or Revision 05 of the service 
bulletin.
    (b) If any discrepancy is found during any inspection required 
by paragraph (a) of this AD, and Airbus Service Bulletin A310-53-
2069, Revision 05, dated November 12, 2002; Revision 04, dated 
November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, 
dated September 23, 1996; or Revision 1, dated September 19, 1995; 
as applicable; specifies to contact Airbus for appropriate action: 
Prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate. Where differences in the compliance times or 
corrective actions exist between the service bulletin and this AD, 
the AD prevails.

New Requirements of This AD

Optional Terminating Action

    (c) Except as provided by paragraph (d) of this AD: 
Accomplishment of the replacement of the stainless steel chafing 
plates with new chafing plates made of aluminum alloy, in accordance 
with Airbus Service Bulletin A310-53-2070, Revision 2, dated 
November 8, 2000; Revision 1, dated September 23, 1996; or the 
original issue, dated October 3, 1994; constitutes terminating 
action for the repetitive inspections required by paragraph (a) of 
this AD.

Continuation of Repetitive Inspections

    (d) Within 30 days after the effective date of this AD: Do a 
review of the airplane maintenance records to determine if any 
corrosion was detected and reworked on the left and/or right side of 
frame 39, stringer 35, during the accomplishment of any corrective 
action or repair specified in paragraphs (a) or (b) of this AD. If 
any corrective action or repair has been accomplished in this area, 
perform an inspection for fatigue cracking of frame 39, stringer 35, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-53-2069, Revision 05, dated November 12, 2002; or 
Revision 04, dated November 8, 2000. Do the initial inspection at 
the threshold specified in Figure 1 of the service bulletin, or 
within 30 days after the effective date of this AD, whichever is 
later. Repeat the inspection thereafter at the intervals specified 
in Figure 1 of the service bulletin. If any discrepancy is found, 
prior to further flight, accomplish the applicable follow-on 
corrective actions, in accordance with the Accomplishment 
Instructions of the service bulletin.

Submission of Information Not Required

    (e) Although the service bulletins referenced in this AD specify 
to submit information to the manufacturer, this AD does not include 
such a requirement.

Alternative Methods of Compliance

    (f) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the Airbus service bulletins specified in 
Table 1 of this AD, as applicable.

      Table 1.--Airbus Service Bulletins Incorporated by Reference
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     Service bulletin--         Revision--              Date--
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A310-53-2069................               1  September 19, 1995.
A310-53-2069................               2  September 23, 1996.

[[Page 41403]]

 
A310-53-2069................              03  October 28, 1997.
A310-53-2069................              04  November 8, 2000.
A310-53-2069................              05  November 12, 2002.
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    (1) The incorporation by reference of the Airbus Service 
Bulletins in Table 2 of this AD, which contain the following 
effective pages, are approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51:

                        Table 2.--New Airbus Service Bulletins Incorporated by Reference
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    Service bulletin, date, and                                Revision level
          revision level--                 Page no.--         shown on page--         Date shown on page--
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A310-53-2069, Revision 2, September  1-6, 9, 10............                  2  September 23, 1996.
 23, 1996.
                                     7, 8, 11-59...........                  1  September 19, 1995.
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A310-53-2069, Revision 03, October   1, 7, 15, 16, 26, 28,                  03  October 28, 1997.
 28, 1997.                            29-34, 43-61.
                                     2-6, 9, 10............                  2  September 23, 1996.
                                     8, 11-14, 17-25, 27,                    1  September 19, 1995.
                                      35-42.
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A310-53-2069, Revision 04, 2000      1-57..................                 04  November 8, 2000.
 November 8, 2000.
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A310-53-2069, Revision 05, November  1-12, 20, 21, 23......                 05  November 12, 2002.
 12, 2002.
                                     13-19, 22, 24-57......                 04  November 8, 2000.
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    (2) The incorporation by reference of Airbus Service Bulletin 
A310-53-2069, Revision 1, dated September 19, 1995, was approved 
previously by the Director of the Federal Register as of June 3, 
1998 (63 FR 23377, April 29, 1998).
    (3) 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 2000-514-326(B) R1, dated May 15, 2002.

Effective Date

    (h) This amendment becomes effective on August 13, 2004.

    Issued in Renton, Washington, on June 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-15373 Filed 7-8-04; 8:45 am]
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