### 30268 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations

List of Subjects in 5 CFR Part 875

Administrative practices and procedures, Employee benefit plans, Government contracts, Government employees, Health insurance, Military personnel, Organization and functions, Retirement.

U.S. Office of Personnel Management. John Berry,

Director.

■ Accordingly, OPM amends 5 CFR part 875, as follows:

**PART 875—FEDERAL LONG TERM CARE INSURANCE PROGRAM** 

■ 1. The authority citation for 5 CFR part 875 continues to read as follows:

Authority: Authority: 5 U.S.C. 9008.

■ 2. Add a new § 875.213 to subpart B to read as follows:

**§ 875.213 May I apply as a qualified relative if I am the domestic partner of an**  **employee or annuitant?**

(a) You may apply for coverage as a qualified relative if you are a domestic partner, as described in paragraph (b) of this section. As prescribed by OPM, you will be required to provide documentation to demonstrate that you meet these requirements.

(b) For purposes of this part, the term

‘‘ domestic partner’’ is a person in a domestic partnership with an employee or annuitant of the same sex. The term

‘‘ domestic partnership ’’ is defined as a committed relationship between two adults, of the same sex, in which the partners—

(1) Are each other’s sole domestic partner and intend to remain so indefinitely;

(2) Have a common residence, and intend to continue the arrangement indefinitely;

(3) Are at least 18 years of age and mentally competent to consent to a contract;

(4) Share responsibility for a significant measure of each other’s financial obligations;

(5) Are not married to anyone else; (6) Are not a domestic partner of anyone else;

(7) Are not related in a way that, if they were of opposite sex, would prohibit legal marriage in the State in which they reside; and

(8) Certify that they understand that willful falsification of the documentation described in paragraph (a) of this section may lead to disciplinary action and the recovery of the cost of benefits received related to such falsification and may constitute a criminal violation under 18 U.S.C. 1001. [FR Doc. 2010–13015 Filed 5–28–10; 8:45 am]

**BILLING CODE 6325–39–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0235; Directorate Identifier 2010–CE–010–AD; Amendment**  **39–16311; AD 2010–11–06]**

**RIN 2120–AA64**

**Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd**  **Models N22B, N22S, and N24A Airplanes** 

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

**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) 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:

The results of full scale fatigue tests being conducted by the manufacturer have shown the need for inspection of critical fastener holes in the stub wing upper front spar cap, near the wing strut attachment. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective July 6, 2010.

On July 6, 2010, 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 the Docket 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 :**  Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; e-mail: doug.rudolph@faa.gov.

**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 March 9, 2010 (75 FR 10694), and proposed to supersede AD 97–11–12, Amendment 39–10041 (62 FR 28997, May 29, 1997). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

The results of full scale fatigue tests being conducted by the manufacturer have shown the need for inspection of critical fastener holes in the stub wing upper front spar cap, near the wing strut attachment.

Amendment 1 adopts the manufacturer’s latest service bulletin. Its new inspection method avoids having to remove the Huck bolts and the potential to damage the holes. 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 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 25 products of U.S. registry. We alsoestimate that it will take about 2 workhours 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 $4,250, or $170 per product.

In addition, we estimate that any necessary follow-on actions will take


### 30269 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations

about 4 work-hours and require parts costing $2,500, for a cost of $2,840 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 removing Amendment 39–10041 (62 FR 28997, May 29, 1997), and adding the following new AD:
2010–11–06 AeroSpace Technologies of Australia Pty Ltd: Amendment 39– 16311; Docket No. FAA–2010–0235; Directorate Identifier 2010–CE–010–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective July 6, 2010.

Affected ADs

(b) This AD supersedes AD 97–11–12, Amendment 39–10041.
Applicability

(c) This AD applies to Models N22B, N22S, and N24A airplanes, all serial numbers, certificated in any category.
Subject

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

Reason

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

The results of full scale fatigue tests being conducted by the manufacturer have shown the need for inspection of critical fastener holes in the stub wing upper front spar cap, near the wing strut attachment.

Amendment 1 adopts the manufacturer’s latest service bulletin. Its new inspection method avoids having to remove the Huck bolts and the potential to damage the holes.
Actions and Compliance

(f) Unless already done, do the following actions in accordance with Nomad Service Bulletin NMD–53–22, dated June 4, 2007:

(1) Within the next 100 hours time-inservice (TIS) after July 6, 2010 (the effective date of this AD), or within the next 90 days after July 6, 2010 (the effective date of this AD), whichever occurs first, install aninspection hole in the left-hand and righthand stub wing bottom skin. (2) Before further flight after installing the inspection hole required in paragraph (f)(1) of this AD, initially inspect the stub wing front spar cap for cracks. Repetitively thereafter inspect at intervals not to exceed every 600 hours TIS.

(3) If any crack is found during any inspection required in paragraph (f)(2) of this AD, before further flight contact Customer Support Manager, Gippsland Aeronautics Pty Ltd., P.O. Box 881, MORWELL, Victoria, 3040, Australia; phone: +61 3 5172 1200; fax: +61 3 5172 1201; e-mail: support@gippsaero.com, for an FAAapproved repair scheme/modification and incorporate the repair scheme/modification. Due to FAA policy, the repair scheme/ modification for crack damage must include an immediate repair of the crack. The repair scheme cannot be by repetitive inspection only. The repair scheme/modification may incorporate repetitive inspections in addition to the repetitive inspections required in paragraph (f)(2) of this AD. Continued operational flight with un-repaired crack damage is not permitted.

FAA AD Differences

Note: This AD differs from the MCAI and/or service information as follows: The MCAI states to follow the service bulletin. The service bulletin does not specifically call out a corrective action if cracks are found. The FAA is including specific instruction of corrective action in the AD.

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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090. Before using any approved AMOC on any airplane 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.

(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

(h) Refer to MCAI Civil Aviation Safety Authority (CASA) AD GAF–N22–52, Amendment 1, dated January 2010; and


### 30270 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations

Nomad Service Bulletin NMD–53–22, dated June 4, 2007, for related information.
Material Incorporated by Reference

(i) You must use Nomad Service Bulletin NMD–53–22, dated June 4, 2007, 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 Gippsland Aeronautics Pty Ltd., Latrobe Regional Airport, P.O. Box 881, Morwell Victoria, 3840, Australia; phone: +61 3 5172 1200; fax: +61 3 5172 1201; Internet: www.gippsaero.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 May 13, 2010. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–12176 Filed 5–28–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0219; Directorate Identifier 2010–NE–14–AD; Amendment 39–**  **16315; AD 2010–11–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Turbomeca Astazou XIV B and XIV H Turboshaft**  **Engines**

**AGENCY :**  Federal Aviation Administration (FAA), 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: Investigation of an uncommanded in-flight shutdown (IFSD) revealed that a third stage turbine wheel rupture was not contained by the turbine casings. The released portion consisted of a turbine blade together with the rim piece immediately below the blade. The rim piece was bounded by two adjacent axial slots and a fatigue crack that had developed between the holes in which the slots terminate. The slots and holes, which are closed by riveted plugs, were introduced by modification AB 173 in order to improve the vibration characteristics of the turbine wheel. Modification AB 208 brings an improvement to modification AB 173 by changing only the riveting detail. SN 283 72 0805 provides instructions for re-boring the holes at overhaul or repair in order to improve their surface condition. A manufacturing process modification has been introduced to improve the surface condition of these holes in third stage turbine wheels. Wheels subject to the improved manufacturing process have S/Ns outside the range specified in Table 1. Although there is only one known event, and although it resulted only in an uncommanded IFSD, with no damage to the aircraft, the possibility exists that additional events may occur, potentially involving damage to the aircraft. We are issuing this AD to prevent uncontained failures of the third stage turbine wheel, which could result in damage to the helicopter.

**DATES :**  This AD becomes effective July 6, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 6, 2010.

**ADDRESSES :**  The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC
20590–0001.

**FOR FURTHER INFORMATION CONTACT :**  Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117, fax (781)
238–7199.

**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 March 30, 2010 (75 FR 15627). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that:

Investigation of an uncommanded IFSD revealed that a third stage turbine wheel rupture was not contained by the turbine casings. The released portion consisted of a turbine blade together with the rim piece immediately below the blade. The rim piece was bounded by two adjacent axial slots and a fatigue crack that had developed between the holes in which the slots terminate. The slots and holes, which are closed by riveted plugs, were introduced by modification AB 173 in order to improve the vibration characteristics of the turbine wheel. Modification AB 208 brings an improvement to modification AB 173 by changing only the riveting detail. SB 283 72 0805 provides instructions for re-boring the holes at overhaul or repair in order to improve their surface condition. A manufacturing process modification has been introduced to improve the surface condition of these holes in third stage turbine wheels. Wheels subject to the improved manufacturing process have S/Ns outside the range specified in Table 1. Although there is only one known event, and although it resulted only in an uncommanded IFSD, with no damage to the aircraft, the possibility exists that additional events may occur, potentially involving damage to the aircraft.

To address the unsafe condition, EASA issued AD 2009–0136, mandating inspection of certain third stage turbine wheels and removal of any damaged wheel. The wheels to be inspected were those whose cycles since new (CSN) would exceed 2,000 by February 1, 2011. Following additional research by Turbomeca on crack initiation and growth, this AD mandates inspections based on new criteria and removal of any damaged wheel.

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. Costs of Compliance

Based on the service information, we estimate that this AD will affect about three Astazou engines installed on products of U.S. registry. We alsoestimate that it will take about 5 workhours per engine to comply with this AD. The average labor rate is $85 per work-hour. We anticipate no parts to be required. Based on these figures, we estimate the cost of the AD on U.S. operators to be $1,275. 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.