[Federal Register Volume 69, Number 143 (Tuesday, July 27, 2004)]
[Rules and Regulations]
[Pages 44592-44594]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-16675]


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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