This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. 

# Rules and Regulations Federal Register 

### 61975

Vol. 75, No. 194

Thursday, October 7, 2010

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0644; Directorate Identifier 2009–NM–204–AD; Amendment**  **39–16466; AD 2010–21–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A300 B4–600 Series Airplanes, Model**  **A300 B4–600R Series Airplanes, Model A300 C4–605R Variant F Airplanes, and**  **Model A300 F4–600R Series Airplanes (Collectively Called A300–600 Series**  **Airplanes)**

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

**ACTION :**  Final rule.

**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:

Within the framework of the A300–600 aircraft Service Life Extension programme (42,500 FC [flight cycles]), it has been concluded that a reinforcement of the junction of frame bases at FR48, FR49 and FR51 to FR53 is necessary to enable the aircraft to reach the Extended Service Goal (ESG).

* * * [Failure of the frame base], if not corrected, could affect the structural integrity of the fuselage.
* * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective November 12, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 12, 2010.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

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 July 1, 2010 (75 FR 38061). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Within the framework of the A300–600 aircraft Service Life Extension programme (42,500 FC [flight cycles]), it has been concluded that a reinforcement of the junction of frame bases at FR48, FR49 and FR51 to FR53 is necessary to enable the aircraft to reach the Extended Service Goal (ESG).

* * * [Failure of the frame base], if not corrected, could affect the structural integrity of the fuselage.

For the reasons described above, this AD requires the reinforcement of the affected junction of frame bases. Required actions include doing a dimensional measurement of the holes, and doing corrective actions if necessary; doing an eddy current inspection of the holes for cracking, and doing corrective actions if necessary; and doing cold expansion of the holes and installing fasteners. Corrective actions include contacting Airbus for repair instructions and doing the repair. 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 considered the comment received. The commenter supports the NPRM. Change to Compliance Time Specified in Paragraph (h) of This AD

We have revised paragraph (h) of this AD by adding the compliance time

‘‘within 100 flight cycles after the effective date of this AD ’’ to the sentence ending with ‘‘ accomplish those instructions. ’’ We have evaluated the data and determined that adding this compliance time will not adversely affect safety.

Conclusion

We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This 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 our FAA policies. Any such differences are highlighted in a Note within the AD.
Costs of Compliance

We estimate that this AD will affect 122 products of U.S. registry. We alsoestimate that it will take about 81 workhours 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 $12,300 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 do not 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 $2,340,570, or $19,185 per product.


### 61976 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations

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.
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, 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. 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:

2010–21–06 Airbus: Amendment 39–16466. Docket No. FAA–2010–0644; Directorate Identifier 2009–NM–204–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 12, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, and B4–622R airplanes; Model A300 C4– 605R Variant F airplanes; and Model A300 F4–605R and F4–622R airplanes; certificated in any category; on which modification 12699 has not been completed.
Subject

(d) Air Transport Association (ATA) of America Code 53: Fuselage.

Reason

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

Within the framework of the A300–600 aircraft Service Life Extension programme (42,500 FC [flight cycles]), it has been concluded that a reinforcement of the junction of frame bases at FR48, FR49 and FR51 to FR53 is necessary to enable the aircraft to reach the Extended Service Goal (ESG).

* * * [Failure of the frame base], if not corrected, could affect the structural integrity of the fuselage.
* * * * *
Compliance

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

Actions

(g) Except for airplanes identified in paragraph (h) of this AD: At the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, reinforce the junctions of frame bases FR48, FR49, FR51, FR52 and FR53, which includes doing a dimensional measurement of the holes, doing an eddy current inspection of the holes for cracking, doing a cold expansion of the holes, installing fasteners, and doing applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6161, Revision 02, dated October 16, 2009. If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.

(1) For airplanes on which Airbus Modification No. 03986 has been accomplished as of the effective date of this AD: Before the accumulation of 37,600 total flight cycles.

(2) For airplanes on which Airbus Modification No. 03986 has not been accomplished as of the effective date of this AD: Before the accumulation of 28,900 total flight cycles.

(h) For airplanes modified prior to the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6161, dated February 13, 2009; or Revision 01, dated June 24, 2009: Within 10 days after the effective date of this AD, prior to doing any cold working process, determine if an eddy current inspection for cracking has been done, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6161, Revision 02, dated October 16, 2009. If the eddy current inspection has not been done, or it cannot be proven that it has been done, contact Airbus for instructions and accomplish those instructions within 100 flight cycles after the effective date 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

(i) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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 FAAapproved if they are approved by the State of Design Authority (or their delegated


### 61977 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations

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 (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(j) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009–0188, dated August 26, 2009; and Airbus Mandatory Service Bulletin A300–53–6161, Revision 02, dated October 16, 2009; for related information.
Material Incorporated by Reference

(k) You must use Airbus Mandatory Service Bulletin A300–53–6161, Revision 02, including Appendix 01, dated October 16, 2009 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—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; e-mail: account.airwortheas@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.

(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 September 23, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–25017 Filed 10–6–10; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0552; Directorate Identifier 2009–NM–095–AD; Amendment**  **39–16464; AD 2010–21–04]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747–100, 747–200B,**  **and 747–200F Series Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  The FAA is superseding two existing airworthiness directives (ADs), which apply to certain Model 747–100, 747–200B, and 747–200F series airplanes. The existing ADs currentlyrequire inspections to detect fatiguerelated skin cracks and corrosion of the skin panel lap joints in the fuselage upper lobe, and repair if necessary. One of the existing ADs, AD 94–12–09, also requires modification of certain lap joints and inspection of modified lap joints. The other AD, AD 90–15–06, requires repetitive detailed external visual inspections of the fuselage skin at the upper lobe skin lap joints for cracks and evidence of corrosion, and related investigative and corrective actions. This AD reduces the maximum interval of the post-modification inspections, and adds post-repair inspection requirements for certain airplanes. This AD results from reports of cracking on modified airplanes. We are issuing this AD to detect and correct fatigue cracking and corrosion in the fuselage upper lobe skin lap joints, which could lead to rapid decompression of the airplane and inability of the structure to carry fail-safe loads.

**DATES :**  This AD becomes effective November 12, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 12, 2010.

**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

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 90–15–06, Amendment 39–6653 (55 FR 28600, July 12, 1990), and AD 94–12–09, Amendment 39–8937 (59 FR 30285, June 13, 1994). The existing ADs apply to certain Model 747–100, 747–200B, and 747–200F series airplanes. That NPRM was published in the Federal Register on June 22, 2010 (75 FR 35356). That NPRM proposed to continue to require inspections to detect fatigue-related skin cracks and corrosion of the skin panel lap joints in the fuselage upper lobe, and repair if necessary; modification of certain lap joints and inspection of modified lap joints; and repetitive detailed external visual inspections of the fuselage skin at the upper lobe skin lap joints for cracks and evidence of corrosion, and related investigative and corrective actions. That NPRM also proposed to reduce the maximum interval of the post-modification inspections, and adds post-repair inspection requirements for certain airplanes.

Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the NPRM. Request to Correct Typographical Error in Paragraph (l) of the NPRM

Boeing requests that we revise paragraph (l) of the NPRM to change the numeral ‘‘ 1 ’’ to the letter ‘‘ l ’’ to correctly identify the paragraph references.

We agree and have corrected the typographical error accordingly.