AD 2013-02-11

We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This AD was prompted by a report of an analysis that demonstrated a reduced fatigue life for the side link bolts, center sway link bolts, and thrust link bolts on the forward engine mounts. This AD requires repetitive replacement of those bolts. We are issuing this AD to prevent deterioration of the structural integrity of the bolts, which could result in possible damage to an engine or wing.

Final rule.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. The FAA amends Sec. 39.13 by adding the following new AD:

2013-02-11 Airbus: Amendment 39-17332. Docket No. FAA-2012-1071; Directorate Identifier 2012-NM-070-AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective March 8, 2013.

(b) Affected ADs

None.

(c) Applicability

This AD applies to all Airbus Model A310-203 airplanes, certificated in any category.

(d) Subject

Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

This AD was prompted by a report of an analysis that demonstrated a reduced fatigue life for the side link bolts, center sway linkbolts, and thrust link bolts on the forward engine mounts. We are issuing this AD to prevent deterioration of the structural integrity of the bolts, which could result in possible damage to an engine or wing.

(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Actions

Within 18 months after the effective date of this AD, replace all side link bolts on left hand (LH) and right hand (RH) side of the engines, and all center sway link bolts and thrust link bolts of both engines, having any part number (P/N) identified in paragraphs (g)(1) through (g)(6) of this AD, with new bolts having the same part number, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-71-2037, including Appendices 01 and 02, dated September 30, 2011. Repeat the bolt replacements thereafter at intervals not exceeding 134 months.
(1) P/N 9021M88P01.
(2) P/N 9021M88P02.
(3) P/N 9205M81P01.
(4) P/N 9021M88P03.
(5) P/N 9021M88P04.
(6) P/N 9205M82P01.

(h) Other FAA AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone (425) 227-2125; fax (425) 227-1147. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(i) Related Information

Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2012-0056, dated April 3, 2012; and Airbus Mandatory Service Bulletin A310-71-2037, including Appendices 01 and 02, dated September 30, 2011; for related information.

(j) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A310-71-2037, including Appendices 01 and 02, dated September 30, 2011.
(ii) Reserved.
(3) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated by reference 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/cfr/ibr-locations.html.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 16, 2012 (77 FR 63268). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI) states:

Post type-certification analyses performed in the frame of the Extended Service Goal (ESG) exercise, demonstrated a reduced fatigue life for the side link bolts, centre sway link bolts and thrust link bolts of the General Electric (GE) CF6-80A3 forward engine mounts.
This condition, if left uncorrected, could result in a deterioration of the structural integrity of the front engine mount bolts [and possible damage to an engine or wing].
For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires [repetitive] replacement of all side link bolts, centre sway link bolts and all thrust link bolts of GE CF6- 80A3 powered aeroplanes.

You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 63268, October 16, 2012) or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD will affect 30 products of U.S. registry. We also estimate that it will take about 139 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $4,810 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we donot control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $498,750, or $16,625 per product.

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 determined that this AD will not have federalism implications under Executive Order 13132. This AD 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.

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For the reasons discussed above, I certify that this AD:
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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 AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM (77 FR 63268, October 16, 2012), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.