### 29205 Federal Register / Vol. 80, No. 98 / Thursday, May 21, 2015 / Rules and Regulations

insurers of individual (non-group) policies of liability insurance that are issued to and in the name of the enrollee or a covered family member.

(d) A FEHB carrier’s exercise of its right to pursue and receive subrogation or reimbursement recoveries does not give rise to a claim within the meaning of 5 CFR 890.101 and is therefore not subject to the disputed claims process set forth at 5 CFR 890.105.

(e) Any subrogation or reimbursement recovery on the part of a FEHB carrier shall be effectuated against the recovery first (before any of the rights of any other parties are effectuated) and is not impacted by how the judgment, settlement, or other recovery is characterized, designated, or apportioned.

(f) Pursuant to a subrogation or reimbursement clause, the FEHB carrier may recover directly from any party that may be liable, or from the covered individual, or from any applicable insurance policy, or a workers’ compensation program or insurance policy, all amounts available to or received by or on behalf of the covered individual by judgment, settlement, or other recovery, to the extent of the amount of benefits that have been paid or provided by the carrier.

(g) Any contract must contain a provision incorporating the carrier’s subrogation and reimbursement rights as a condition of and a limitation on the nature of benefits or benefit payments and on the provision of benefits under the plan’s coverage. The corresponding health benefits plan brochure must contain an explanation of the carrier’s subrogation and reimbursement policy.

(h) A carrier’s rights and responsibilities pertaining to subrogation and reimbursement under any FEHB contract relate to the nature, provision, and extent of coverage or benefits (including payments with respect to benefits) within the meaning of 5 U.S.C. 8902(m)(1). These rights and responsibilities are therefore effective notwithstanding any state or local law, or any regulation issued thereunder, which relates to health insurance or plans.

[FR Doc. 2015–12378 Filed 5–20–15; 8:45 am]

**BILLING CODE 6325–63–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 23**

**[Docket No. CE306; Special Conditions No. 23–246–SC]** 

**Special Conditions: Cirrus Design Corporation Model SF50 airplane; Full**  **Authority Digital Engine Control (FADEC) System; Withdrawal** 

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

**ACTION :**  Final special conditions; withdrawal.

**SUMMARY :**  The FAA is withdrawing a previously published document granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing Special Condition No. 23–246–SC through mutual agreement with Cirrus Design Corporation.

**DATES :**  Effective May 21, 2015, the special condition published on April 20, 2010 (75 FR 20518) is withdrawn.

**FOR FURTHER INFORMATION CONTACT :**  Jeff Pretz, Federal Aviation Administration, Small Airplane Directorate, Aircraft Certification Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 329–3239; facsimile (816) 329– 4090, email jeff.pretz@faa.gov.

**SUPPLEMENTARY INFORMATION :**  Background

On September 9, 2008, Cirrus Design Corporation applied for a type certificate for their new model SF50 aircraft. Under the provisions of 14 CFR part 21, § 21.17, Cirrus Design Corporation must show that the model SF50 meets the applicable provisions of part 23, as amended by amendments 23–1 through 23–59.

On April 20, 2010, the FAA published Special Condition No. 23–246–SC for the Cirrus Design Corporation modelSF50 airplane. The Cirrus SF50 is a lowwing, five-plus-two-place (2 children), single-engine turbofan-powered aircraft. The airplane engine is controlled by an Electronic Engine Control (EEC), also known as a Full Authority Digital Engine Control (FADEC).

On December 11, 2012 Cirrus Design Corporation elected to adjust the certification basis of the SF50 to include 14 CFR part 23 through amendment 62. Special Condition No. 23–246–SC is therefore being withdrawn. It no longer reflects the appropriate part 23 amendment level of the aircraft and the basic Special Condition requirement for EEC equipped aircraft has been revised. Reason for Withdrawal The FAA is withdrawing Special Condition No. 23–246–SC because Cirrus Design Corporation elected to revise the model SF50 certification basis to amendment 23–62.

The authority citation for this Special Condition withdrawal is 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.17; and 14 CFR 11.38 and 11.19.

Conclusion

Withdrawal of this special condition does not preclude the FAA from issuing another document on the subject matter in the future or committing the agency to any future course of action.

Issued in Kansas City, Missouri on May 11,
2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–12262 Filed 5–20–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1570; Directorate Identifier 2014–SW–054–AD; Amendment**  **39–18161; AD 2015–10–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Helicopters (Previously Eurocopter**  **France) Helicopters**

**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 Airbus Helicopters (previously Eurocopter France) Model AS365N3, EC155B, and EC155B1 helicopters with an external life raft in the footsteps with certain part-numbered junction units. This AD requires inspecting the junction units of the external life raft deployment system for corrosion, removing any corrosion, and performing certain measurements to determine whether the junction unit must be replaced. This AD is prompted by failure of a life raft deployment testand corrosion damage inside the lefthand junction unit. These actions are intended to prevent failure of an external life raft to deploy preventing evacuation of passengers during an
emergency.

**DATES :**  This AD becomes effective June 5, 2015.


### 29206 Federal Register / Vol. 80, No. 98 / Thursday, May 21, 2015 / Rules and Regulations

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of June 5, 2015.

We must receive comments on this AD by July 20, 2015.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.

• Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001.

• Hand Delivery: Deliver to the ‘‘Mail’’ address 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 European Aviation Safety Agency (EASA) AD, the economic evaluation, any incorporated by reference service information, 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 service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641– 0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.airbushelicopters.com/techpub

. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is also available on the Internet at http:// www.regulations.gov in Docket No. FAA–2015–1570.

**FOR FURTHER INFORMATION CONTACT :**  Martin R. Crane, Aviation Safety Engineer, Regulations Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5112; email martin.r.crane@ faa.gov

. **SUPPLEMENTARY INFORMATION :** 
Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments.

Discussion

We are adopting a new AD for Airbus Helicopters (previously Eurocopter France) Model AS365N3, EC155B, and EC155B1 helicopters with an external life raft in the footsteps with a junction unit, manufacturer part number (P/N) 200197 or P/N 200188 (Airbus Helicopters P/N 704A341302.48 or P/N 704A341302.30), installed. This AD requires inspecting the external life raft deployment system junction unit for corrosion, removing any corrosion, and measuring the clearance between the internal and external pulleys and the junction unit cover. If the clearance exceeds a certain threshold, this AD requires replacing the junction unit. This AD is prompted by failure of the external life raft deployment test and corrosion damage inside the left-hand junction unit, which blocked the deployment handle. These actions are intended to prevent corrosion damage inside a junction unit, which can prevent a deployment handle from functioning correctly and cause failure of an external life raft to deploy, preventing evacuation of passengers during an emergency.

EASA, which is the Technical Agent for the Member States of the European Union, has issued AD No. 2014–0214, dated September 24, 2014, to correct an unsafe condition for Airbus Helicopters Model AS365N3, EC155B, and EC155B1 helicopters with external life rafts in the footsteps with certain part-numbered junction units installed. EASA advises that failure of the external life raft deployment test was reported by a Model AS365 helicopter operator when the affected external life raft underwent a scheduled maintenance. The failure occurred during an attempt to release the life raft by pulling the left-hand internal deployment handle. Subsequent investigations revealed corrosion damage inside the left-hand junction unit, which blocked the deployment handle. The EASA AD requires an inspection of the tensileloads during a functional test of the liferaft system, the junction unit cover for drainage holes, and the junction unit cover for corrosion. The EASA AD also requires measuring operationalclearance of the right-hand and the lefthand junction units of the external life raft deployment system and, depending on the findings, corrective action and reporting the results to Airbus.

FAA’s Determination

These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by the EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs.

Related Service Information Under 1 CFR Part 51

Airbus Helicopters issued Alert Service Bulletin (ASB) No. EC155– 05A027 for the Model EC155B and B1 helicopter and ASB No. AS365–05.00.67 for the Model AS365N3 helicopter. Both ASBs are Revision 1 and dated September 1, 2014. The ASBs specify checking the tensile load during a functional test of the life-raft system, checking that the drainage hole blank is correctly positioned, inspecting the junction units for corrosion, and measuring the operational clearance between the junction unit pulleys and the cover. If necessary, the ASBs call for removing the corrosion from the cover surface or pulleys and replacing the junction unit.

The ASBs state that the life raft deployment test on a Model AS365 helicopter failed when the left-hand internal deployment handle did not function correctly because the handle was blocked by corrosion inside the junction unit. ASB No. EC155–05A027 further states that Model EC155B and B1 helicopters are equipped with similar junction units.

This service information is reasonably available because the interested parties


### 29207 Federal Register / Vol. 80, No. 98 / Thursday, May 21, 2015 / Rules and Regulations

have access to it through their normal course of business or by the means identified in the **ADDRESSES** section of this AD.
AD Requirements

This AD requires, before further flight:

• Inspecting each external life raft deployment system unit for corrosion, and if there is corrosion, either removing the corrosion and applying a protective coating, primer, and paint to the surface or replacing the junction unit with an airworthy junction unit.

• Measuring the diameter of the junction unit cover and of each (internal and external) junction unit pulley for operational clearance. If the clearance is greater than 0.029 inch (0.75 mm), replacing the junction unit with an airworthy junction unit.

• Inspecting the drainage holes on the upper face and the lower surface of the junction unit cover to determine whether they are plugged. This AD requires plugging the drainage hole on the upper face if it is not plugged and removing the plug in the drainage hole on the lower surface if it is plugged.

Differences Between This AD and the EASA AD

The EASA AD requires a tensile load inspection and, depending on the results of the inspection, may allow a longer compliance time for the remaining required actions. This AD does not require the tensile load inspection and requires all required actions before further flight. The EASA AD allows the operational clearance measurements to be taken before any corrosion is removed, while this AD requires removing any corrosion before taking measurements. The EASA AD requires reporting the inspection results to the manufacturer; this AD does not. Costs of Compliance

There are no costs of compliance with this AD because there are no helicopters equipped with the life raft deployment system that is the subject of this AD.
FAA’s Justification and Determination of the Effective Date

There are no helicopters with the affected life raft deployment system; therefore, we believe it is unlikely that we will receive any adverse comments or useful information about this AD from U.S. Operators.

Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are unnecessary because there are no helicopters with the affected life raft deployment system and that good cause exists for making this amendment effective in less than 30 days.
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, I certify that 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);

3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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.
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 airworthiness directive (AD): 2015–10–05 Airbus Helicopters (previously Eurocopter France): Amendment 39– 18161; Docket No. FAA–2015–1570; Directorate Identifier 2014–SW–054–AD.
(a) Applicability

This AD applies to Model AS365N3, EC155B, and EC155B1 helicopters with an external life raft in the footstep installed with a junction unit, manufacturer part number (P/N) 200197 or P/N 200188 (Airbus Helicopters P/N 704A341302.48 or 704A341302.30), certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as corrosion damage inside a junction unit, which can prevent a deployment handle from functioning correctly. This condition could result in failure of an external life raft to deploy, preventing evacuation of passengers during an emergency.
(c) Effective Date

This AD becomes effective June 5, 2015.
(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Before further flight: (1) Inspect each external life raft deployment system left-hand and right-hand junction unit for corrosion in the areas shown in Figure 3 of Airbus Helicopters Alert Service Bulletin (ASB) No. EC155– 05A027, Revision 1, dated September 1, 2014 (ASB No. EC155–05A027), or ASB No. AS365–05.00.67, Revision 1, dated September 1, 2014, (ASB No. AS365– 05.00.67), as applicable to your helicopter model.

(2) If there is corrosion, either remove the corrosion and apply a protective coating, primer, and paint to the surface or replace the junction unit with an airworthy junction unit.

(3) Measure the diameter of the junction unit cover and of each (internal and external) junction unit pulley for operational clearance. If the clearance is greater than 0.029 inch (0.75 mm) as depicted in Figure 4 of ASB No. EC155–05A027 or Figure 5 of ASB No. AS365–05.00.67, as applicable to your helicopter model, replace the junction unit with an airworthy junction unit.

(4) Inspect the drainage hole on the upper face of the junction unit cover, and if it is unplugged, plug it.

(5) Inspect the drainage hole on the lower surface of the junction unit cover, and if it is plugged, remove the plug.


### 29208 Federal Register / Vol. 80, No. 98 / Thursday, May 21, 2015 / Rules and Regulations

(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin R. Crane, Aviation Safety Engineer, Regulations Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5112; email martin.r.crane@ faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
(g) Additional Information

The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2014–0214, dated September 24, 2014. You may view the EASA AD on the Internet
at http://www.regulations.gov in Docket No. FAA–2015–1570. (h) Subject

Joint Aircraft Service Component (JASC) Code: 2564 Equipment/Furnishing.
(i) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference 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 Helicopters Alert Service Bulletin (ASB) No. EC155–05A027, Revision 1, dated September 1, 2014.

(ii) Airbus Helicopters ASB No. AS365– 05.00.67, Revision 1, dated September 1,
2014.

(3) For Airbus Helicopters service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(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/ibrlocations.html.

Issued in Fort Worth, Texas, on May 11,
2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015–12004 Filed 5–20–15; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 97**

**[Docket No. 31015; Amdt. No. 3641]**

**Standard Instrument Approach Procedures, and Takeoff Minimums**  **and Obstacle Departure Procedures; Miscellaneous Amendments** 

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

**ACTION :**  Final rule.

**SUMMARY :**  This rule establishes, amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures (ODPs) for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

**DATES :**  This rule is effective May 21, 2015. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 21,
2015.

**ADDRESSES :**  Availability of matters incorporated by reference in the amendment is as follows:

For Examination

1. U.S. Department of Transportation, Docket Ops–M30, 1200 New Jersey Avenue SE., West Bldg., Ground Floor, Washington, DC 20590–0001.

2. The FAA Air Traffic Organization Service Area in which the affected airport is located;

3. The office of Aeronautical Navigation Products, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or,

4. 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. Availability
All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit the National Flight Data Center at fdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from the FAA Air Traffic Organization Service Area in which the affected airport is located.

**FOR FURTHER INFORMATION CONTACT :**  Richard A. Dunham III, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) Telephone: (405) 954–4164.

**SUPPLEMENTARY INFORMATION :**  This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or removes SIAPS, Takeoff Minimums and/or ODPS. The complete regulatory description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part § 97.20. The applicable FAA forms are FAA Forms 8260–3, 8260–4, 8260–5, 8260–15A, and 8260–15B when required by an entry on 8260–15A.

The large number of SIAPs, Takeoff Minimums and ODPs, their complex nature, and the need for a special format make publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their graphic depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on FAA form documents is unnecessary. This amendment provides the affected CFR sections and specifies the types of SIAPs, Takeoff Minimums and ODPs with their applicable effective dates. This amendment also identifies the airport and its location, the procedure, and the amendment number. Availability and Summary of Material Incorporated by Reference

The material incorporated by reference is publicly available as listed in the **ADDRESSES** section.

The material incorporated by reference describes SIAPS, Takeoff