AD 2004-15-07

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.

Final rule.

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 eddycurrent (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 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_federa_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.

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 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

TheFAA 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 willnot 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

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.

39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive: