71998 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 

accumulation of 3,000 total flight cycles 

since first flight of the airplane, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(3) For Model A319 airplanes, 

manufacturer serial numbers 4151, 4228, and 

4319 (post-modification 28238, 28162, and 

28342): Inspect before the accumulation of 

2,500 total flight cycles since first flight of 

the airplane, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(h) Measurements and Corrective Actions 

If, during any inspection required by 

paragraph (g) of this AD, the fastener is 

determined to be missing, within the 

applicable compliance time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Measure the hole dimensions of the five 

holes surrounding the missing fastener, and 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1242, dated May 

22, 2012; except where the service bulletin 

specifies to contact Airbus, before further 

flight, repair using a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). Do 

all applicable related investigative and 

corrective actions before further flight. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0132, dated 

July 19, 2012, for related information, which 

can be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0096-0002. 

(k) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1242, 

dated May 22, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28170 Filed 11–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0700; Directorate 

Identifier 2013–NM–102–AD; Amendment 

39–17676; AD 2013–24–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

reports of fractured rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. This AD requires repetitive 

inspections for cracking and damage of 

both pilot-side rudder pedal tubes, and 

replacement of affected pilot-side 

rudder bar assemblies if necessary. We 

are issuing this AD to detect and correct 

cracking of both pilot-side rudder pedal 

tubes, which could result in loss of pilot 

rudder pedal input causing reduced yaw 

controllability or a runway excursion. 

DATES: This AD becomes effective 

January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2014. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0700 or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on August 26, 2013 (78 FR 

52712). The NPRM proposed to correct 

an unsafe condition for the specified 

products. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2013–12, dated May 14, 2013 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 


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There have been two in-service reports of 

fracture of rudder pedal tubes installed on 

the pilot-side rudder bar assembly. 

Laboratory examination of the fractured 

rudder pedal tubes found that in both cases, 

the fatigue cracks initiated at the aft taper pin 

holes where the connecting rod fitting is 

attached. Fatigue testing of the rudder pedal 

tubes confirmed that the fatigue cracking is 

due to loads induced during parking brake 

application. Therefore, only the rudder pedal 

tubes on the pilot’s side are vulnerable to 

fatigue cracking as the parking brake is 

primarily applied by the pilot. 

Loss of pilot rudder pedal input during 

flight would result in reduced yaw 

controllability of the aeroplane. Loss of pilot 

rudder pedal input during takeoff or landing 

may lead to a runway excursion. 

This [Canadian] AD mandates initial and 

repetitive [detailed or eddy current] 

inspections [for cracking and damage and 

replacement if necessary] of the pilot-side 

rudder * * * [bar assembly], until the 

terminating action is accomplished. 

Required actions also include 

repairing damage. The terminating 

action is replacement of both pilot-side 

rudder bar assemblies. You may obtain 

further information by examining the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0700- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. 

We received no comments on the 

NPRM (78 FR 52712, August 26, 2013) 

or on the determination of the cost to 

the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

52712, August 26, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 52712, 

August 26, 2013). 

Costs of Compliance 

We estimate that this AD affects 529 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................... 3 work-hours × $85 per hour = $255 per inspection cycle.$0 $255 per inspection 

cycle.

$134,895 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ...................................... 6 work-hours × $85 per hour = $510 ............................................................. $2,850 $3,360 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the repair specified in this 

AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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; 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0700; 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 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


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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 AD: 

2013–24–02 Bombardier, Inc.: Amendment 

39–17676. Docket No. FAA–2013–0700; 

Directorate Identifier 2013–NM–102–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 6, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of 

fractured rudder pedal tubes installed on the 

pilot-side rudder bar assembly. We are 

issuing this AD to detect and correct cracking 

of both pilot-side rudder pedal tubes, which 

could result in loss of pilot rudder pedal 

input causing reduced yaw controllability or 

a runway excursion. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Initial Inspections 

At the applicable time specified in 

paragraphs (g)(1) through (g)(6) of this AD, do 

a detailed or eddy current inspection for 

cracking and damage (i.e., corrosion or 

cracking) of both pilot-side rudder pedal 

tubes having part number (P/N) 600–90204– 

3, in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–162, including Appendix A, dated 

April 5, 2013. 

(1) For airplanes that have accumulated 

less than 20,000 total flight cycles as of the 

effective date of this AD: Do the inspection 

before the accumulation of 23,000 total flight 

cycles. 

(2) For airplanes that have accumulated 

20,000 total flight cycles or more, but less 

than 25,000 total flight cycles as of the 

effective date of this AD: Do the inspection 

within 3,000 flight cycles after the effective 

date of this AD, but not to exceed 26,300 total 

flight cycles. 

(3) For airplanes that have accumulated 

25,000 total flight cycles or more, but less 

than 30,000 total flight cycles as of the 

effective date of this AD: Do the inspection 

within 1,300 flight cycles after the effective 

date of this AD, but not to exceed 30,800 total 

flight cycles. 

(4) For airplanes that have accumulated 

30,000 total flight cycles or more, but less 

than 33,000 total flight cycles as of the 

effective date of this AD: Do the inspection 

within 800 flight cycles after the effective 

date of this AD, but not to exceed 33,500 total 

flight cycles. 

(5) For airplanes that have accumulated 

33,000 total flight cycles or more, but less 

than 37,000 total flight cycles as of the 

effective date of this AD: Do the inspection 

within 500 flight cycles after the effective of 

this AD, but not to exceed 37,300 total flight 

cycles. 

(6) For airplanes that have accumulated 

37,000 total flight cycles or more as of the 

effective date of this AD: Do the inspection 

within 300 flight cycles after the effective 

date of this AD. 

(h) Inspection Definition 

For the purposes of this AD, a detailed 

inspection is an intensive examination of a 

specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as a mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required. 

(i) Repetitive Inspections 

For any tube on which no cracking and no 

damage is found during any inspection 

required by paragraph (g) of this AD: At the 

applicable time specified in paragraph (i)(1) 

or (i)(2) of this AD, repeat the detailed or 

eddy current inspection for cracking of the 

pilot-side rudder pedal tubes, specified in 

paragraph (g) of this AD, until the 

terminating action specified in paragraph (k) 

of this AD has been accomplished. 

(1) If the most recent inspection was a 

detailed inspection: Repeat the inspection 

within 600 flight cycles thereafter. 

(2) If the most recent inspection was an 

eddy current inspection: Repeat the 

inspection within 1,000 flight cycles 

thereafter. 

(j) Corrective Actions 

(1) If any cracking is found around the aft 

tapered holes during any inspection required 

by paragraph (g) or (i) of this AD, before 

further flight, replace the affected rudder bar 

assemblies, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–27–162, including 

Appendix A, dated April 5, 2013. 

(2) If any other damage (i.e., corrosion or 

cracking), other than that specified in 

paragraph (j)(1) of this AD, is found during 

any inspection required by paragraph (g) or 

(i) of this AD, before further flight, repair 

using a method approved by either the 

Manager, New York Aircraft Certification 

Office (ACO), ANE–170, FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

(k) Optional Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–27–162, including 

Appendix A, dated April 5, 2013, terminates 

the inspections required by paragraphs (g) 

and (i) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–12, dated 

May 14, 2013, for related information, which 

can be found in the AD docket on the 

internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0700-0002. 

(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) Bombardier Service Bulletin 601R–27– 

162, including Appendix A, dated April 5, 

2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 


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1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on 

November 15, 2013. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28104 Filed 11–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0449; Airspace 

Docket No. 13–AEA–8] 

Amendment of Class D and E 

Airspace, and Establishment of Class 

E Airspace; Salisbury, MD 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class D 

and Class E airspace, and establishes 

Class E airspace at Salisbury-Ocean City 

Wicomico Regional Airport, Salisbury, 

MD, due to the decommissioning of the 

Salisbury VHF Omnidirectional Radio 

Range Tactical Air Navigation Aid 

(VORTAC) and cancellation of the VOR 

approach. This enhances the safety and 

management of aircraft operations at the 

airport. This action also updates the 

geographic coordinates of the airport, 

and changes the Class D city designator. 

DATES: Effective 0901 UTC, February 6, 

2014. The Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION:

History 

On August 22, 2013, the FAA 

published in the Federal Register a 

notice of proposed rulemaking (NPRM) 

to amend Class D and Class E surface 

area, and establish Class E airspace 

designated as an extension to a Class D 

surface area at Salisbury-Ocean City 

Wicomico Regional Airport, Salisbury, 

MD. (78 FR, 52109). Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on the proposal to the FAA. 

No comments were received. 

Class D and Class E airspace 

designations are published in 

paragraphs 5000, 6002, 6004, and 6005, 

respectively, of FAA Order 7400.9X 

dated August 7, 2013, and effective 

September 15, 2013, which is 

incorporated by reference in 14 CFR 

71.1. The Class D and E airspace 

designations listed in this document 

will be published subsequently in the 

Order. 

The Rule 

This amendment to Title 14, Code of 

Federal Regulations (14 CFR) part 71 

amends Class D airspace and Class E 

surface airspace to within a 4.3-mile 

radius of the airport. Class E airspace 

extending upward from 700 feet above 

the surface is amended to within a 7- 

mile radius of the airport. Class E 

airspace designated as an extension to a 

Class D surface area airspace is 

established within a 4.3-mile radius of 

the airport, with segments extending 7 

miles southeast, northeast, and 

southwest of the airport. The geographic 

coordinates of the airport are adjusted to 

coincide with the FAA’s aeronautical 

database. The Class D city designation is 

changed from Salisbury-Ocean City 

Wicomico Regional Airport, MD, to 

Salisbury, MD. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current, is non-controversial and 

unlikely to result in adverse or negative 

comments. It, therefore, (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 that 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 United States Code. 

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. 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 amends 

controlled airspace at Salisbury-Ocean 

City Wicomico Regional Airport, 

Salisbury, MD. 

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. 

Lists of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (Air). 

Adoption of the Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR Part 71 as follows: 

PART 71—DESIGNATION OF CLASS A, 

B, C, D, AND E AIRSPACE AREAS; AIR 

TRAFFIC SERVICE ROUTES; AND 

REPORTING POINTS 

■ 1. The authority citation for Part 71 

continues to read as follows: 

Authority: 49 U.S.C. 106(g); 40103, 40113, 

40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 

1963 Comp., p. 389. 

§ 71.1 [Amended] 

■ 2. The incorporation by reference in 

14 CFR 71.1 of Federal Aviation 

Administration Order 7400.9X Airspace 

Designations and Reporting Points, 

dated August 7, 2013, effective 

September 15, 2013, is amended as 

follows: 

Paragraph 5000 Class D Airspace 

* * * * * 

AEA MD D Salisbury, MD [Amended] 

Salisbury-Ocean City Wicomico Regional 

Airport, MD 

(Lat. 38°20′25′′ N., long. 75°30′34′′ W.) 

That airspace extending upward from the 

surface to and including 2,500 feet MSL 


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