Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations 45845 

(3) Use paragraph 3.A(2) of CFM Service 

Bulletin (SB) No. CFM56–5 S/B 73–0182, 

Revision 6, dated March 8, 2012, or CFM SB 

No. CFM56–5B S/B 73–0122, Revision 8, 

dated March 8, 2012, to do the inspection. 

(h) Repetitive Inspections 

Repeat the inspection required in 

paragraph (g)(3) of this AD before 10,000 

hours since last overhaul if, after last 

overhaul, the HMU is exposed to TS–1 fuel. 

(i) Credit for Previous Actions 

If the HMU has not been exposed to TS– 

1 fuel since the last overhaul, then the initial 

inspection in paragraph (g) of this AD is not 

required. 

(j) Definitions 

For the purposes of this AD, overhaul is 

defined as HMU maintenance, which 

includes inspection, cleaning, or replacement 

of the HMU delta-P valve. 

(k) Paperwork Reduction Act Burden 

Statement 

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. 

(l) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(m) Related Information 

(1) For more information about this AD, 

contact Martin Adler, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7157; fax: 781–238–7199; 

email: martin.adler@faa.gov. 

(2) Refer to European Aviation Safety 

Agency, AD 2012–0123, dated July 9, 2012, 

for more information. You may examine this 

AD on the Internet at http:// 

www.regulations.gov. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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) CFM International, S. A. (CFM) Service 

Bulletin No. CFM56–5 S/B 73–0182, Revision 

6, dated March 8, 2012. 

(ii) CFM Service Bulletin No. CFM56–5B 

S/B 73–0122, Revision 8, dated March 8, 

2012. 

(3) For CFM International, S. A. service 

information identified in this AD, contact 

CFM International Inc., Aviation Operations 

Center, 1 Neumann Way, M/D Room 285, 

Cincinnati, OH 45125; International phone: 

513–552–3272; USA phone: 877–432–3272; 

International fax: 513–552–3329; USA fax: 

877–432–3329; email: geae.aoc@ge.com; or 

CFM International SA, Customer Support 

Center, International phone: 33 1 64 14 88 66; 

International fax: 33 1 64 79 85 55; email: 

snecma.csc@snecma.fr. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

July 9, 2013. 

Robert J. Ganley, 

Acting Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–17296 Filed 7–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0639; Directorate 

Identifier 2013–SW–020–AD; Amendment 

39–17518; AD 2013–15–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule, request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–10– 

03 for Bell Helicopter Textron 

Helicopters (Bell) Model 204B, 205A, 

205A–1, 205B, 210, 212, 412, 412CF, 

and 412EP helicopters. AD 2008–10–03 

required certain checks and inspections 

of each tail rotor blade assembly (T/R 

blade) at specified intervals and 

repairing or replacing, as applicable, 

any cracked or damaged T/R blade. 

Since we issued AD 2008–10–03, an 

accident attributed to a T/R failure 

occurred. This new AD retains the 

requirements of AD 2008–10–03 and 

adds a second, more detailed inspection 

that allows for an earlier detection of a 

crack or other damage in a T/R blade. 

These actions are intended to prevent a 

failure of the T/R blade and subsequent 

loss of helicopter control. 

DATES: This AD becomes effective 

August 14, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of August 14, 2013. 

We must receive comments on this 

AD by September 30, 2013. 

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 economic 

evaluation, 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 Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

TX 76101; telephone (817) 280–3391; 

fax (817) 280–6466; or at 

www.bellcustomer.com/. You may 

review service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

7-AVS-ASW-170@faa.gov. 

SUPPLEMENTARY INFORMATION:


emcdonald on DSK67QTVN1PROD with RULES
45846 Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations 

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 

On April 22, 2008, we issued AD 

2008–10–03, Amendment 39–15509 (73 

FR 24858, May 6, 2008) for Bell Model 

204B, 205A, 205A–1, 205B, 210, 212, 

412, 412CF, and 412EP helicopters. AD 

2008–10–03 required certain checks and 

inspections of each T/R blade at 

specified intervals and repairing or 

replacing, as applicable, any 

unairworthy T/R blade. AD 2008–10–03 

was prompted by eight reports of fatigue 

cracking of T/R blades installed on Bell 

Model 212 and 412 helicopters (three 

failures on the Bell Model 212 and five 

failures on the Bell Model 412) with a 

T/R blade, part number (P/N) 212–010– 

750–009, –105, and –107. Three of the 

Model 412 failures occurred during 

flight. 

Actions Since AD 2008–10–03 Was 

Issued 

Since we issued AD 2008–10–03 (73 

FR 24858, May 6, 2008), an accident 

attributed to a T/R failure occurred. 

Because of this accident, we have 

determined that a superseding AD is 

necessary to require a second, more 

detailed inspection that allows for an 

earlier detection of a crack or other 

damage. These actions are intended to 

prevent failure of T/R blade and 

subsequent loss of helicopter control. 

This superseding AD does not apply 

to Model 204B helicopters because 

those helicopters do not have the 

affected T/R blades installed and should 

not have been included in the 

applicability of AD 2008–10–03. We are 

no longer requiring a daily check of the 

T/R blades because we have determined 

that the additional, more detailed 

inspection and the sequence of the 

inspections provide an appropriate level 

of safety. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Related Service Information 

On February 4, 2013, Bell issued Alert 

Service Bulletin (ASB) No. 205–13–109 

for Model 205A and 205A–1 

helicopters; ASB No. 205B–13–61 for 

Model 205B helicopters; ASB No. 212– 

13–147 for Model 212 helicopters; ASB 

412–13–155 for Model 412 and 412EP 

helicopters; and ASB No. 412CF–13–52 

for 412CF helicopters. All ASBs are 

dated February 4, 2013. Bell reported 

that it recently examined a fractured T/ 

R blade and that the fracture originated 

from surface damage. ASB No. 205–13– 

109, No. 205B–13–61, and No. 412CF– 

13–52 describe procedures for a 3X 

magnifying glass inspection of the entire 

T/R blade surface for damage every 25 

hours time-in-service (TIS), similar to 

that required by AD 2008–10–03 (73 FR 

24858, May 6, 2008). ASB No. 212–13– 

147 and No. 412–13–155 do not include 

this 3X visual inspection, because that 

inspection has been incorporated into 

the maintenance manual for these 

models. All five of the ASBs introduce 

an additional local visual inspection 

with a10X magnifying glass of each T/ 

R blade between blade station 20.00 to 

35.00 from the leading edge to the 

trailing edge. Bell added a reminder to 

operators that it is critical to investigate 

any paint and skin imperfections should 

the inspection warrant such action. If 

any skin damage exceeds the limits in 

the applicable Maintenance Manual, the 

ASBs call for removing the T/R blade 

from service. 

AD Requirements 

This AD supersedes AD 2008–10–03 

(73 FR 24858, May 6, 2008) and requires 

for any Model 205A, 205A–1, 205B, 210, 

212, 412, 412CF, and 412EP helicopter 

with certain T/R blades the following 

actions: 

Within 25 hours TIS or 30 days, 

whichever occurs first, and thereafter at 

intervals not to exceed 25 hours TIS or 

30 days, whichever occurs first, 

cleaning and visually inspecting each T/ 

R blade assembly for a crack, corrosion, 

nick, scratch, or dent using a 3X or 

higher power magnifying glass and a 

bright light; and 

Visually inspecting certain parts of 

each T/R blade for a crack or other 

damage using a 10X or higher power 

magnifying glass and a bright light, and 

if damage exists, measuring the depth of 

any damage. 

Before further flight, replacing any 

cracked T/R blade and repairing or 

replacing any damaged T/R blade. 

Replacing a blade with T/R blade, P/ 

N 412–016–100–111, on eligible 

helicopters is terminating action for the 

inspection requirements of this AD. 

Differences Between the AD and the 

Service Information 

This AD differs from the ASBs 

because we include Model 210 

helicopters. The Model 210 helicopter 

has the same part-numbered blades as 

the other applicable helicopter models. 

Costs of Compliance 

We estimate that this AD affects 80 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs to comply with this AD: 

Visually inspecting a blade (2 per 

helicopter) for a crack or other damage 

will require .25 work-hour. No parts are 

needed. For the expected 12 annual 

inspections, the total cost per helicopter 

will be $510 a year, and $40,800 for the 

U.S. fleet. 

Replacing a T/R assembly will require 

6 work-hours for a labor cost of $510. 

Parts will cost $23,048, bringing the 

total cost to $23,558 per helicopter. 

According to the Bell’s service 

information, some of the cost may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control the 

warranty coverage by Bell. Accordingly, 

we have included all costs in our cost 

estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the required corrective 

actions must be accomplished within 25 

hours TIS or 30 days, whichever comes 

first, a very short time period based on 

the average flight-hour utilization rate of 

these helicopters. These helicopters are 


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Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations 45847 

typically used for logging, firefighting, 

and lifting and carrying external loads. 

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 impracticable 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 the 

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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 airworthiness directive (AD) 

2008–10–03, Amendment 39–15509 (73 

FR 24858, May 6, 2008), and adding the 

following new AD: 

2013–15–02 BELL HELICOPTER 

TEXTRON: Amendment 39–17518; 

Docket No. FAA–2013–0639; Directorate 

Identifier 2013–SW–020–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

(Bell) Model 205A, 205A–1, 205B, 210, 212, 

412, 412CF, and 412EP helicopters with a tail 

rotor blade assembly (T/R blade), part 

number (P/N) 210–010–001–(all dash 

numbers) or 212–010–750–(all dash 

numbers), certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking of a T/R blade, which could 

lead to failure of the T/R blade and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD No. 2008–10–03, 

Amendment 39–15509 (73 FR 24858, May 6, 

2008). 

(d) Effective Date 

This AD becomes effective August 14, 

2013. 

(e) 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. 

(f) Required Actions 

(1) Within 25 hours time-in-service (TIS) or 

30 days, whichever occurs first, and 

thereafter at intervals not to exceed 25 hours 

TIS or 30 days, whichever occurs first: 

(i) Clean each T/R blade by hand using a 

mild soap and cheesecloth (C–486) on both 

sides of the blade in a spanwise direction and 

dry thoroughly. 

(ii) Using a 3X or higher power magnifying 

glass and a bright light, visually inspect the 

T/R blade skins, leading edge spar, doublers, 

grip plates, and trailing edge on both sides 

of each blade for a crack, corrosion (may be 

indicated by blistering, peeling, flaking, 

bubbling, or cracked paint), a nick, scratch, 

dent, or other damage. Pay particular 

attention to both sides of the T/R blade in the 

area located 16 to 35 inches from the T/R 

blade tip (blade station 20.00 to 35.00—the 

T/R blade tip is located at blade station 51) 

as shown by the shaded area of Figure 1 of 

Bell Alert Service Bulletin (ASB) No. 205– 

13–109; ASB No. 205B–13–61; ASB No. 212– 

13–147; ASB 412–13–155; or ASB No. 

412CF–13–52, all dated February 4, 2013, as 

applicable to your helicopter. Also, pay 

particular attention to the inboard blade butt 

area near the attachment of the external 

balance weight and screws, and to any blade 

surface that was snagged by cheesecloth, as 

that may be an indication of a crack or paint 

chip that could lead to corrosion. 

Note 1 to Paragraph (f) of this AD: Figure 

1 of the Bell ASB No. 205–13–109; ASB No. 

205B–13–61; ASB No. 212–13–147; ASB 

412–13–155; and ASB No. 412CF–13–52, all 

dated February 4, 2013, show the shaded area 

as part of the 10X inspection only. This AD 

requires the shaded area to be inspected 

during both the 3X and 10X inspections. 

(iii) Using a 10X or higher magnifying glass 

and a bright light, visually inspect both sides 

of each blade for a crack or other damage 

between blade station 20.00 to 35.00 as 

shown by the shaded area of Figure 1 of Bell 

ASB No. 205–13–109; ASB No. 205B–13–61; 

ASB No. 212–13–147; ASB 412–13–155; or 

ASB No. 412CF–13–52, all dated February 4, 

2013, as applicable to your helicopter. 

(iv) If any blistering, peeling, flaking, 

bubbling, or cracked paint is detected 

anywhere on the blade, remove the paint 

from the affected area by sanding in a 

spanwise direction with abrasive cloth or 

paper (C–406) 240-grit or finer, and a final 

sanding using abrasive cloth or paper (C–406) 

400-grit or finer. Visually inspect the affected 

area for any corrosion or a crack using a 10X 

or higher magnifying glass and a bright light. 

If any corrosion is found, measure the depth 

of the damage. (A digital optical micrometer 

is one tool that can be used for this 

measurement.) 

(v) If a nick, scratch, or dent is found 

anywhere on the blade, visually inspect for 

a crack using a 10X or higher power 

magnifying glass and a bright light. Measure 

the depth of the damage. (A digital optical 

micrometer is one tool that can be used for 

this measurement.) 

(2) Before further flight: 

(i) Replace with an airworthy blade any 

T/R blade that has a crack or that has any 

corrosion, nick, scratch, dent, or other 

damage that exceeds any of the maximum 

repair limits. 

(ii) Repair or replace with an airworthy 

blade any T/R blade that has any corrosion, 

nick, scratch, dent or other damage that is 

within the maximum repair limits. 

(3) Replacing a T/R blade with T/R blade, 

P/N 412–016–100–111, on eligible helicopter 

models is considered terminating action to 

this AD. 

(g) Special Flight Permit 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 


emcdonald on DSK67QTVN1PROD with RULES
45848 Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5170; 

email 7-AVS-ASW-170@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. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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) Bell ASB No. 205–13–109, dated 

February 4, 2013. 

(ii) Bell ASB No. 205B–13–61, dated 

February 4, 2013. 

(iii) Bell ASB No. 212–13–147, dated 

February 4, 2013. 

(iv) Bell ASB No. 412–13–155, dated 

February 4, 2013. 

(v) Bell ASB No. 412CF–13–52, dated 

February 4, 2013. 

(3) For Bell service information identified 

in this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101; 

telephone (817) 280–3391; fax (817) 280– 

6466; or at www.bellcustomer.com/. 

(4) You may view this service information 

that is incorporated by reference in the AD 

Docket on the Internet at http:// 

www.regulations.gov. 

(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 July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–18079 Filed 7–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–1303; Airspace 

Docket No. 12–ANM–29] 

Amendment of Class E Airspace; Salt 

Lake City, UT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class E 

airspace at Salt Lake City, UT, to 

accommodate aircraft using Area 

Navigation (RNAV) Global Positioning 

System (GPS) and Instrument Landing 

System (ILS) or Localizer (LOC) 

standard instrument approach 

procedures at Salt Lake City 

International Airport. This improves the 

safety and management of Instrument 

Flight Rules (IFR) operations at the 

airport. This action also adjusts the 

geographic coordinates of the airport, 

and makes a minor change to the legal 

description of Class E airspace 

extending upward from 1,200 feet above 

the surface, at Salt Lake City, UT. 

DATES: Effective date, 0901 UTC, 

October 17, 2013. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA, 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

History 

On May 13, 2013, the FAA published 

in the Federal Register a notice of 

proposed rulemaking (NPRM) to modify 

controlled airspace at Salt Lake City, UT 

(78 FR 27872). Interested parties were 

invited to participate in this rulemaking 

effort by submitting written comments 

on the proposal to the FAA. No 

comments were received. 

Subsequent to publication, the FAA’s 

Aeronautical Products Office requested 

the phrase in the regulatory text ‘‘. . . 

excluding that portion within Restricted 

Area R–6403.’’ be moved from the 

13,500 foot airspace and incorporated 

into the 1,200 foot airspace. With the 

exception of editorial changes and the 

changes described above, this rule is the 

same as that proposed in the NPRM. 

Class E airspace designations are 

published in paragraph 6005, of FAA 

Order 7400.9W dated August 8, 2012, 

and effective September 15, 2012, which 

is incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 

listed in this document will be 

published subsequently in that Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) Part 71 by 

modifying Class E airspace extending 

upward from 700 feet above the surface, 

at Salt Lake City International Airport, 

Salt Lake City, UT, to accommodate IFR 

aircraft executing RNAV (GPS) and ILS 

or LOC standard instrument approach 

procedures at the airport. This action 

removes reference to the exclusion of 

the Price, UT; Delta, UT; and Evanston, 

WY, airspace area, and the Bonneville, 

UT 1,200 foot Class E airspace area, and 

enhances the safety and management of 

aircraft operations at the airport. The 

geographic coordinates of the airport are 

adjusted in accordance with the FAA’s 

aeronautical database. 

The FAA has determined this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that only affects air traffic 

procedures and air navigation, it is 

certified this rule, when promulgated, 

does not have a significant economic 

impact on a substantial number of small 

entities under the criteria of the 

Regulatory Flexibility Act. The FAA’s 

authority to issue rules regarding 

aviation safety is found in Title 49 of the 

U.S. Code. Subtitle 1, Section 106 

discusses the authority of the FAA 

Administrator. Subtitle VII, Aviation 

Programs, describes in more detail the 

scope of the agency’s authority. This 

rulemaking is promulgated under the 

authority described in Subtitle VII, Part 

A, Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it modifies 

controlled airspace at Salt Lake City 

International Airport, Salt Lake City, 

UT. 

Environmental Review 

The FAA has determined that this 

action qualifies for categorical exclusion 

under the National Environmental 

Policy Act in accordance with FAA 

Order 1050.1E, ‘‘Environmental 

Impacts: Policies and Procedures,’’ 

paragraph 311a. This airspace action is 

not expected to cause any potentially 

significant environmental impacts, and 

no extraordinary circumstances exist 

that warrant preparation of an 

environmental assessment. 


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