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

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 model 

SF50 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 test 

and 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. 

mstockstill on DSK4VPTVN1PROD with RULES