### 74608 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations

(b) * * * (1) * * * (iii) Determine the dollar value on the posting date of the number of shares the participant would have received had the contributions or loan payments been made on time. If the contributions or loan payments would have been invested in a Lifecycle fund that is retired on the posting date, the constructed share price shall equal the retired Lifecycle fund share price on December 31 of the retirement year, multiplied by the current L Income Fund share price, divided by the L Income Fund share price on December 31 of the retirement year. The dollar value shall be the number of shares the participant would have received had the contributions or loan payments been made on time multiplied by the constructed share price.

(iv) The difference between the dollar value of the contribution or loan payment on the posting date and the dollar value of the contribution or loan payment on the ‘‘as of ’’ date is the breakage.

* * * * *

■ 3. Amend § 1605.12, by revising paragraph (c)(2)(ii) to read as follows:

**§ 1605.12 Removal of erroneous contributions.** 

* * * * *

(c) * * * (2) * * * (ii) Multiply the price per share on the date the adjustment is posted by the number of shares calculated in paragraph (c)(2)(i) of this section. If the contribution was erroneously contributed to a Lifecycle fund that is retired on the date the adjustment is posted, the price per share shall equal the retired Lifecycle fund share price on December 31 of the retirement year, multiplied by current L Income Fund share price, divided by the L Income Fund share price on December 31 of the retirement year.

* * * * * [FR Doc. 2010–29886 Filed 11–30–10; 8:45 am]

**BILLING CODE 6760–01–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0735 Directorate Identifier 2010–CE–030–AD; Amendment**  **39–16529; AD 2010–24–10]**

**RIN 2120–AA64**

**Airworthiness Directives; CENTRAIR Models 101, 101A, 101P, and 101AP**  **Gliders**

**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) issued 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:

Damages to the rudder bar locking adjustment tube of a non-reinforced version have been reported to Socie  ́ te

 ́ Nouvelle (SN) Centrair. This tube had been reinforced in 1984 with a modification. Gliders produced before the introduction of this modification have not been systematically retrofitted.

In case of rudder bar locking adjustment tube breaking in flight when adjusting the rudder pedals position, it might interfere with the rudder pedals which could lead to rudder jam or a restricted rudder movement and consequently, to reduced control of the sailplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective January 5, 2011.

On January 5, 2011, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at 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 service information identified in this AD, contact Socie  ́ te

 ́ Nouvelle CENTRAIR, Aerodome—36300 Le Blanc, France; telephone: +33 (0)254 370796; fax: +33 (0)54. 374864; Internet: http://www.societe.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148.

**FOR FURTHER INFORMATION CONTACT :**  Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816)
329–4090.

**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 23, 2010 (75 FR 43103). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI, issued on May 26, 2010, states:

Damages to the rudder bar locking adjustment tube of a non-reinforced version have been reported to Socie  ́ te

 ́ Nouvelle (SN) Centrair. This tube had been reinforced in 1984 with a modification. Gliders produced before the introduction of this modification have not been systematically retrofitted.

In case of rudder bar locking adjustment tube breaking in flight when adjusting the rudder pedals position, it might interfere with the rudder pedals which could lead to rudder jam or a restricted rudder movement and consequently, to reduced control of the sailplane.

For the reason described above, this AD requires inspecting the rudder bar locking adjustment tube and, if necessary, replacing it. 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 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.

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


### 74609 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations

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. Costs of Compliance

We estimate that this AD will affect 52 products of U.S. registry. We alsoestimate that it will take about 1 workhour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour.

Based on these figures, we estimate the cost of this AD on U.S. operators to be $4,420 or $85 per product.

In addition, we estimate that any necessary follow-on actions will take about 1 work-hour and require parts costing $51, for a cost of $136 per product. We have no way of determining the number of products that may need these actions. 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 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 Management Facility 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 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:

2010–24–10 CENTRAIR: Amendment 39– 16529; Docket No. FAA–2010–0735; Directorate Identifier 2010–CE–030–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective January 5, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to CENTRAIR Models 101, 101A, 101P, and 101AP gliders, all serial numbers, certificated in any category.
Subject

(d) Air Transport Association of America (ATA) Code 27: Flight Controls.

Reason

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

Damages to the rudder bar locking adjustment tube of a non-reinforced version have been reported to Socie  ́ te

 ́ Nouvelle (SN) Centrair. This tube had been reinforced in 1984 with a modification. Gliders produced before the introduction of this modification have not been systematically retrofitted.

In case of rudder bar locking adjustment tube breaking in flight when adjusting the rudder pedals position, it might interfere with the rudder pedals which could lead to rudder jam or a restricted rudder movement and consequently, to reduced control of the sailplane.

For the reason described above, this AD requires inspecting the rudder bar locking adjustment tube and, if necessary, replacing it. Actions and Compliance

(f) Unless already done, do the following actions in accordance with Socie  ́ te

 ́ Nouvelle Centrair Service Bulletin No. 101–29, dated July 30, 2009:

(1) Within the next 30 days after January 5, 2011 (the effective date of this AD), inspect the rudder bar locking adjustment tube to determine if it has been reinforced and to determine if it has been damaged.

(2) If the results of the inspection required in paragraph (f)(1) of this AD show that the rudder bar locking adjustment tube has not been reinforced and is not damaged, replace it with a reinforced rudder bar locking adjustment tube, part number (P/N) $Y186A, at the next scheduled maintenance event after January 5, 2011 (the effective date of this AD) but no later than 12 months after January 5, 2011 (the effective date of this AD).

(3) If the results of the inspection required in paragraph (f)(1) of this AD show that the rudder bar locking adjustment tube has not been reinforced but is damaged, replace it with a reinforced rudder bar locking adjustment tube, P/N $Y186A, before further flight.

FAA AD Differences

Note: 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, Standards Office, 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: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329– 4090. Before using any approved AMOC on any glider to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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.


### 74610 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations

(3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,
AES–200.

Related Information

(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2010–0099, dated May 26, 2010; and Socie  ́ te

 ́ Nouvelle Centrair Service Bulletin No. 101–29, dated July 30, 2009, for related information.
Material Incorporated by Reference

(i) You must use Socie  ́ te

 ́ Nouvelle Centrair Service Bulletin No. 101–29, dated July 30, 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 Socie  ́ te

 ́ Nouvelle CENTRAIR, Aerodome—36300 Le Blanc, France; telephone: +33 (0)254 370796; fax: +33 (0)54. 374864; Internet: http://
www.societe.com.

(3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768.

(4) You may also review copies of the service information incorporated by reference for this AD 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 Kansas City, Missouri, on November 17, 2010. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–29461 Filed 11–30–10; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–1067; Directorate Identifier 2009–NM–071–AD; Amendment**  **39–16516; AD 2010–23–26]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C,**  **B4–103, and B4–203 Airplanes; and Model A300 B4–601, B4–603, B4–620,**  **B4–622, B4–605R, B4–622R, and F4– 605R Airplanes** 

**AGENCY :**  Federal Aviation Administration, Department of Transportation.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing 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:

Following the occurrence of cracks on theMLG [main landing gear] rib 5 RH [righthand] and LH [left-hand] attachment fitting lower flanges, DGAC [Direction Ge  ́ ne

 ́ rale de l’Aviation Civile] France AD 2003–318(B) [parallel to part of FAA AD 2006–12–13] was issued to require repetitive inspections and, as terminating action * * *[.]

Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300– 600 type aeroplanes on which the terminating action * * * [was] embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes.
* * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective January 5, 2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 5, 2011.

On July 18, 2006 (71 FR 33994, June 13, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.

On April 12, 2000 (65 FR 12077, March 8, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.

**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 November 18, 2009 (74 FR 59483), and proposed to supersede AD 2006–12–13, Amendment 39–14639 (71 FR 33994, June 13, 2006). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

Following the occurrence of cracks on theMLG [main landing gear] rib 5 RH [righthand] and LH [left-hand] attachment fitting lower flanges, DGAC [Direction Ge  ́ ne

 ́ rale de l’Aviation Civile] France AD 2003–318(B) [parallel to part of FAA AD 2006–12–13] was issued to require repetitive inspections and, as terminating action, the embodiment of Airbus Service Bulletins (SB) A300–57–0235 and A300–57–6088 * * *.

Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300– 600 type aeroplanes on which the terminating action SB’s were embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes.

To address and correct this condition, Airbus developed an inspection programme for aeroplanes modified in accordance with SB A300–57–0235 or A300–57–6088. This inspection programme was required to be implemented by DGAC France AD F–2005– 113, original issue and later revision 1 [parallel to part of FAA AD 2006–12–13].

A new EASA [European Aviation Safety Agency] AD 2008–0111, superseding DGAC France AD F–2005–113R1, was issued to reduce the applicability. For aeroplanes already compliant with DGAC France AD F– 2005–113R1, no further action was required.

Since EASA AD 2008–0111 issuance, Airbus reviewed the inspection programmes of SB A300–57A0246 and SB A300–57A6101 to introduce repetitive inspections including a new inspection technique for holes 47 and 54 and to reduce inspections threshold and intervals from 700 Flight Cycles (FC) to 400 FC until a revised terminating action is made available.

For the reasons stated above, AD 2009– 0081 superseded EASA AD 2008–0111 and required operators to comply with the new inspection programme introduced in