### 22422 Federal Register / Vol. 74, No. 91 / Wednesday, May 13, 2009 / Rules and Regulations

CalaverasMadera (Only includes Yosemite National Park portion.) Mariposa Merced Stanislaus Tuolumne

* * * * * [FR Doc. E9–11193 Filed 5–12–09; 8:45 am]

**BILLING CODE 6325–39–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0433; Directorate Identifier 2009–NM–003–AD; Amendment**  **39–15902; AD 2009–10–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A380–841, –842, and –861 Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6).

These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring.

This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground.

* * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective May 28, 2009.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 28, 2009.

We must receive comments on this AD by June 12, 2009. **ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 this AD, 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.

**FOR FURTHER INFORMATION CONTACT :**  Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008–0216, dated December 9, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6).

These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring.

This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground.

To prevent the risk of a MFTF#6 detachment, this Airworthiness Directive (AD) requires an inspection program in order to detect cracks [and delamination] before they become critical and in case of findings to replace the MFTF#6 [with a new or serviceable part]. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued Service Bulletin A380–57–8014, including Appendix 01, dated November 21, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the AD.

FAA’s Determination of the Effective Date

Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and


### 22423 Federal Register / Vol. 74, No. 91 / Wednesday, May 13, 2009 / Rules and Regulations

opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2009–0433; Directorate Identifier 2009–NM–003– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. 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.

For the reasons discussed above, I certify 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); 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 AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

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

■ 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. The FAA amends § 39.13 by adding the following new AD:

2009–10–07 Airbus: Amendment 39–15902. Docket No. FAA–2009–0433; Directorate Identifier 2009–NM–003–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective May 28, 2009.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A380– 841, –842 and –861 airplanes, certificated in any category, all serial numbers.
Subject

(d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

(e) The mandatory continued airworthiness information (MCAI) states:

‘‘During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6).

‘‘These cracks were located at the pivot attachment support-ring and at the

‘‘U–frame in the attachment area to aftkinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring.

‘‘This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground.

‘‘To prevent the risk of a MFTF#6 detachment, this Airworthiness Directive (AD) requires an inspection program in order to detect cracks [and delamination] before they become critical and in case of findings to replace the MFTF#6 [with a new or serviceable part].’’ Actions and Compliance (f) Unless already done, do the following: (1) At the applicable time specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD for the left- and right-hand MFTF#6, do a special detailed (ultrasonic and high-frequency eddy current) inspection of the filet radii of pivot supports, monolithic carbon fibre reinforced plastic structures, and radii of U–Frame, and a general visual inspection of MFTF#6, for cracking and delamination, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380–57–8014, dated November 21, 2008.

(i) For Model A380–841 and –842 airplanes: Before the MFTF#6 has accumulated 500 total flight cycles since its first installation on an airplane, or within 30 flight hours after the effective date of this AD, whichever occurs later.

(ii) For Model A380–861 airplanes: Before the MFTF#6 has accumulated 100 total flight cycles since its first installation on an airplane, or within 30 flight hours after the effective date of this AD, whichever occurs later.

(2) If no cracking and no delamination are detected during any inspection required by paragraph (f)(1) of this AD, repeat the inspections required by paragraph (f)(1) of this AD thereafter at intervals not to exceed the applicable time specified in paragraph (f)(2(i) or (f)(2)(ii) of this AD.

(i) For Model A380–841 and –842 airplanes: 50 flight cycles.

(ii) For Model A380–861 airplanes: 10 flight cycles.

(3) If any cracking or delamination is found during any inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the MFTF#6 with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380–57–8014, dated November 21, 2008, and repeat the inspections specified in paragraph (f)(1) of this AD at the applicable time defined in paragraph (f)(2) of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No Differences.

Other FAA AD Provisions

(g) 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. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District


### 22424 Federal Register / Vol. 74, No. 91 / Wednesday, May 13, 2009 / Rules and Regulations

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 FAAapproved 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.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2008–0216, dated December 9, 2008; and Airbus Service Bulletin A380–57–8014, dated November 21, 2008; for related information.
Material Incorporated by Reference

(i) You must use Airbus Service Bulletin A380–57–8014, including Appendix 01, dated November 21, 2008, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Airbus SAS–EANA (Airworthiness Office); 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253; Fax +33 562 110 307; e-mail account.airworthA380@airbus.com; Internet http:// www.airbus.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221 or 425–227–1152.

(4) You may also review copies of the 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/ code

_of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on May 1,
2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–10934 Filed 5–12–09; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0135; Directorate Identifier 2008-NM–170-AD; Amendment 39–**  **15901; AD 2009–10–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Boeing Model 747–400 and 747–400D Series**  **Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Boeing Model 747–400 and 747–400D series airplanes. This AD requires repetitive inspections to detect cracks in the floor panel attachment fastener holes of the Section 41 upper deck floor beam upper chords, and related investigative and corrective actions if necessary. This AD results from reports of cracks found in the Section 41 upper deck floor beam upper chords. We are issuing this AD to detect and correct cracks in these chords, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.

**DATES :**  This AD is effective June 17,
2009.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 17, 2009.

**ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com

. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 747–400 and 747– 400D series airplanes. That NPRM was published in the Federal Register on February 18, 2009 (74 FR 7573). That NPRM proposed to require repetitive inspections to detect cracks in the floor panel attachment fastener holes of the Section 41 upper deck floor beam upper chords, and related investigative and corrective actions if necessary.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comment received. Boeing supports the NPRM.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed.
Costs of Compliance

We estimate that this AD affects 53 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD.