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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2008-1201; Directorate Identifier 2008-NM-007-AD]

RIN ID: RIN 2120-AA64

NOTICE: PROPOSED RULES

ACTION: Airworthiness Directives:

DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).

SUBJECT CATEGORY: Airworthiness Directives; Airbus Model A310 Series Airplanes

DATES: We must receive comments on this proposed AD by December 15, 2008.

DOCUMENT SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A310 series airplanes. The existing AD currently requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; repetitive inspections for fatigue cracking of frame 39, stringer 35; and corrective actions if necessary. The existing AD also provides for an optional terminating action for certain repetitive inspections, except for certain areas where corrosion was detected and reworked. This proposed AD would reduce the intervals for accomplishing repetitive inspections in a certain area. This proposed AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are proposing this AD 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.

SUMMARY: Airbus Model A310 Series Airplanes,

SUPPLEMENTAL INFORMATION

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA20081201; Directorate Identifier 2008NM007AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On June 29, 2004, we issued AD 20041406, amendment 3913715 (69 FR 41401, July 9, 2004), for certain Airbus Model A310 series airplanes. That AD 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. The existing AD also provides for an optional terminating action for repetitive inspections, except for certain areas where corrosion was detected and reworked. That AD resulted from reports of the presence of corrosion under the chafing plates and around the fasteners of the wing root between fuselage frames 36 and 39. We issued that AD 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.

Actions Since Existing AD Was Issued

Since we issued AD 20041406, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has informed us that, as a result of A310 extended service goal activities, the repetitive intervals for existing repetitive inspections in a certain area, as required by AD 20041406, must be reduced to adequately address the identified unsafe condition. Relevant Service Information

Airbus has issued Revision 06 of Service Bulletin A310532069, dated May 22, 2007 (AD 20041406 refers to Airbus Service Bulletin A310532069, Revision 1, dated September 19, 1995, through Revision 05, dated November 12, 2002, as appropriate sources of service information for accomplishing the required inspections and corrective actions). The inspection and corrective actions procedures specified in Revision 06 are essentially identical to those specified in Revision 1 through Revision 05. Revision 06 reduces the thresholds and repetitive intervals for the inspections that are required after corrosion has been found and reworked. The new thresholds range between 70 [[Page 67111]]
and 28,000 flight cycles or between 250 and 103,500 flight hours, whichever occurs first, depending on the depth of the rework. The new intervals range between 70 and 17,300 flight cycles or between 250 and 63,900 flight hours, whichever occurs first. No additional work is required by Revision 06 for airplanes inspected in accordance with Revision 1 through Revision 05. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated Service Bulletin A310532069, Revision 06, and issued airworthiness directive 20070292, dated November 27, 2007, to ensure the continued airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

These airplanes are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ``Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,'' dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA's findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States.

This proposed AD would supersede AD 20041406 and would continue to require repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; repetitive inspections for fatigue cracking of frame 39, stringer 35; and corrective actions if necessary. This proposed AD also would continue to provide for an optional terminating action for certain repetitive inspections, except for certain areas where corrosion was detected and reworked. In addition, this proposed AD would reduce the intervals for accomplishing the repetitive inspections in a certain area.

Differences Between Proposed AD and Service Bulletin

Revision 06 of Service Bulletin A310532069 specifies to contact the manufacturer for thresholds and repeat intervals for inspections under certain conditions, but this proposed AD would require those intervals be approved by the FAA or the EASA (or its delegated agent). In light of the type of inspections that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, thresholds and repetitive intervals approved by the FAA or the EASA would be acceptable for compliance with this proposed AD.

Change to Existing AD

This proposed AD would retain all requirements of AD 20041406. Since AD 20041406 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
Corresponding requirement Requirement in AD 20041406 in this proposed AD paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
paragraph (d)............................. paragraph (i).
paragraph (e)............................. paragraph (j).

Costs of Compliance

This proposed AD would affect about 69 Model A310 series airplanes of U.S. registry.

The actions that are required by AD 20041406 and retained in this proposed AD take about 68 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $375,360, or $5,440 per airplane, per inspection cycle.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.

For the reasons discussed above, I certify that the proposed regulation:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the 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.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39AIRWORTHINESS 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 3913715 (69 FR 41401, July 9, 2004) and adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA20081201; Directorate Identifier 2008NM 007AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December 15, 2008.
Affected ADs
(b) This AD supersedes AD 20041406.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes, certificated in any category,
[[Page 67112]]
on which Airbus Modifications 8888 and 8889 have not been
accomplished.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD 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. Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Requirements of AD 20041406
Repetitive Inspections and Corrective Actions
(f) Except as provided by paragraphs (g), (k), and (l) of this

FOR FURTHER INFORMATION CONTACT Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271138; fax (425) 2271149.