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. 

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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 tensile 

loads 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 operational 

clearance 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 

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

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. 

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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 

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