70046 Federal Register / Vol. 76, No. 218 / Thursday, November 10, 2011 / Rules and Regulations 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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. 

(3) Reporting Requirements: 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. 

Related Information 

(j) Refer to MCAI EASA Airworthiness 

Directive 2010–0138, dated July 1, 2010; 

Avions de Transport Re ́gional Service 

Bulletin ATR42–55–0014, dated May 11, 

2010; and Avions de Transport Re ́gional 

Service Bulletin ATR72–55–1006, dated May 

11, 2010; for related information. 

Material Incorporated by Reference 

(k) You must use Avions de Transport 

Re ́gional Service Bulletin ATR42–55–0014, 

dated May 11, 2010; or Avions de Transport 

Re ́gional Service Bulletin ATR72–55–1006, 

dated May 11, 2010; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on October 

27, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–28752 Filed 11–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1158; Directorate 

Identifier 2010–SW–018–AD; Amendment 

39–16847; AD 2011–22–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS350B, B1, B2, B3, BA, 

C, D, and D1; and AS355E, F, F1, F2, 

N, and NP Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the Eurocopter France (Eurocopter) 

Model AS350B, B1, B2, B3, BA, C, D, 

and D1 helicopters; and Model AS355E, 

F, F1, F2, and N helicopters with certain 

tail rotor pitch control rods installed. 

That AD requires a daily check of the 

tail rotor (T/R) pitch control rod (control 

rod) outboard spherical bearing 

(bearing) for play. If play exists, that AD 

requires measuring the bearing’s radial 

and axial play. Since that AD was 

issued, an incident occurred where the 

pilot of a Model AS350 helicopter felt 

vibrations in the anti-torque pedal in 

flight, resulting in a precautionary 

landing. An investigation determined 

that the control rod showed extensive 

wear on the ball-joint. This superseding 

AD maintains the requirements of the 

existing AD, and expands the 

applicability to include the Model 

AS355NP helicopter and additional 

part-numbered control rods. The actions 

specified by this AD are intended to 

prevent failure of a control rod, loss of 

T/R control, and subsequent loss of 

control of the helicopter. 

DATES: Effective November 25, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

January 9, 2012. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http:// 

www.eurocopter.com/techpub. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 


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FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Manager, FAA, Rotorcraft 

Directorate, Safety Management Group, 

2601 Meacham Blvd., Fort Worth, TX 

76137, telephone (817) 222–5126, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 22, 2003, the FAA issued 

AD 2003–22–06, Amendment 39–13354 

(68 FR 61608, October 29, 2003), Docket 

2000–SW–12–AD (AD 2003–22–06), for 

Eurocopter Model AS350B, B1, B2, B3, 

BA, C, D, and D1; and Model AS355E, 

F, F1, F2, and N helicopters with 

control rods, part-number (P/N) 

350A33–2145–00 or 350A33–2145–01, 

which superseded AD 98–24–35, 

Amendment 39–10921 (63 FR 66418, 

December 2, 1998), Docket 98–SW–41– 

AD, issued November 19, 1998 (AD 98– 

24–35). AD 98–24–35 required a 

recurring inspection to measure the 

control rod bearing for radial and axial 

play. That action was prompted by an 

accident and separate incident 

involving Model AS350B2 helicopters, 

and investigations revealed a broken 

control rod on the helicopter that was 

involved in the accident, and a severely 

worn control rod on the helicopter 

involved in the incident. There were 

two other unconfirmed incidents cited 

by the National Transportation Safety 

Board (based on the manufacturer’s 

reports) involving the same control rod, 

P/N 350A33–2145–01. AD 2003–22–06 

superseded AD 98–24–35, and requires 

a daily check of the control rod bearing, 

allows a larger axial play limit, and 

requires a more frequent inspection 

interval once play is found in the 

control rod bearing during a daily 

check. AD 2003–22–06 also added the 

Eurocopter Model AS350B3 helicopter 

and another part-numbered control rod 

to the applicability. AD 2003–22–06 was 

prompted by a review of additional 

service information and public 

comments regarding the requirements of 

AD 98–24–35. The actions specified by 

AD 2003–22–06 are intended to prevent 

separation of the bearing ball from its 

outer race, rubbing of the body of the 

control rod against the tail rotor blade 

pitch horn clevis, failure of a control 

rod, loss of T/R control, and subsequent 

loss of control of the helicopter. 

Actions Since Issuing Previous AD 

Since issuing AD 2003–22–06 (68 FR 

61608, October 29, 2003), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union, has 

issued EASA AD No. 2010–0006, dated 

January 7, 2010, to correct an unsafe 

condition for the Eurocopter Model 

AS350B, B1, B2, B3, BA, BB, and D 

helicopters; and Model AS355E, F, F1, 

F2, and N, and NP helicopters with 

control rods, P/N 350A33–2100–00, –01, 

–02, –03, or –04; P/N 350A33–2121–00, 

–01, or –02; P/N 350A33–2143–00; or P/ 

N 350A33–2145–00 or –01. EASA 

advises that a pilot of a Eurocopter 

Model AS350 helicopter felt slight 

vibrations in the pedal unit in flight. A 

few minutes later, the vibration level 

increased and the pilot carried out a 

precautionary autorotation landing. 

After landing, it was discovered that one 

TR pitch-change link was damaged, the 

tailboom cone was missing, and there 

was an impact mark on the tailboom. 

Further investigation revealed the 

affected TR pitch-change link showed 

extensive wear on the ball-joint. EASA 

advises that this condition, if not 

detected and corrected, could lead to 

loss of the anti-torque function and 

possible loss of control of the helicopter. 

In addition, after further review of the 

language used to describe the unsafe 

condition addressed in AD 2003–22–06 

(68 FR 61608, October 29, 2003), it has 

been determined that changes are 

needed in terminology to more 

accurately describe the unsafe condition 

that this AD is intending to correct. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. 05.00.60 for the 

Model AS350 series helicopters, and 

ASB No. 05.00.56 for the Model AS355 

series helicopters, both dated December 

9, 2009. These ASBs specify performing 

an initial and recurring check for play 

in the pitch-change links. If axial play 

in the ball-joint is detectable, the ASBs 

specify removing the pitch-change link 

and measuring the bearing wear using a 

dial indicator. The EASA classified 

these ASBs as mandatory and issued 

EASA AD No. 2010–0006 to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Determination and Requirements 

of This AD 

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, their 

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 EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. Therefore, this 

AD is being issued to prevent failure of 

a control rod, loss of tail rotor control, 

and subsequent loss of control of the 

helicopter. This AD requires the 

following actions: 

• Before the first flight of each day, 

check the control rod bearing for play 

on the helicopter, by observation and 

feel, by slightly moving the TR blade in 

the flapping axis while monitoring the 

bearing for movement. This action may 

be performed by an owner/operator 

(pilot) holding at least a private pilot 

certificate, and must be entered into the 

helicopter maintenance records in 

accordance with 14 CFR 43.9(a)(1)–(4) 

and 91.417(a)(2)(v). A pilot may perform 

this check because it involves only a 

visual and physical check of the control 

rod for play, and can be performed 

equally well by a pilot or a mechanic. 

If play is detected, a mechanic must 

remove the control rod from the 

helicopter, and using a dial indicator, 

measure the control rod bearing wear. If 

the radial play exceeds 0.008 inch or 

axial play exceeds 0.016 inch, the 

control rod must be replaced with an 

airworthy control rod before further 

flight. 

• Thereafter, at recurring intervals not 

to exceed 30 hours time-in-service (TIS), 

remove the control rod and measure the 

bearing wear using a dial indicator. If 

the radial play exceeds 0.008 inch or 

axial play exceeds 0.016 inch, replace 

the control rod with an airworthy 

control rod before further flight. 

The short compliance time involved, 

before the first flight of each day, is 

required because the previously 

described critical unsafe condition can 

adversely affect the controllability of the 

helicopter. Therefore, this AD must be 

issued immediately. Since a situation 

exists that requires the immediate 

adoption of this regulation, it is found 

that notice and opportunity for prior 

public comment hereon are 

impracticable, and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Differences Between This AD and the 

EASA AD 

This AD differs from the EASA AD as 

follows: 

• This AD includes the Model 

AS350C and AS350D1 helicopters, as 

they may have the same control rod; this 

AD does not include the Model 

AS350BB because it does not have an 

FAA-issued type certificate. 

• This AD uses the term ‘‘T/R pitch 

control rod’’ and the EASA AD uses the 

term ‘‘T/R pitch change link’’ to 

describe the same part. 

• This AD uses the term ‘‘loss of 

T/R control’’ to describe the unsafe 

condition, and the EASA AD uses the 

term ‘‘loss of anti-torque control.’’ 


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• This AD uses the term ‘‘hours TIS’’ 

to describe compliance times, and the 

EASA AD uses the term ‘‘flight hours.’’ 

• This AD requires either a pilot/ 

operator or mechanic, before the first 

flight of each day, to perform a check or 

inspection of the bearing for play. If 

play is found, a mechanic must, before 

further flight, measure the bearing play, 

and thereafter measure the bearing play 

at intervals not to exceed 30 hours TIS. 

The EASA AD requires a mechanic, 

within 30 flight hours, to perform an 

initial inspection to measure the bearing 

play, and thereafter, at intervals not to 

exceed 30 flight hours. The EASA AD 

does not require a daily check. 

Costs of Compliance 

We estimate that this AD will affect 

about 733 helicopters of U.S. registry. 

We estimate, per helicopter, it will take 

minimal work-hours to do the daily 

check, 1 work-hour to do the recurring 

inspection, and 1 work-hour to replace 

1 control rod. The average labor rate is 

$85 per work-hour. Required parts will 

cost about $1,724 to replace a control 

rod per helicopter. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators is $1,949,047 per year, 

assuming 10 recurring inspections per 

year per helicopter, and assuming 1 

control rod is replaced per year per 

helicopter. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2011–1158; 

Directorate Identifier 2010–SW–018– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19476). 

Regulatory Findings 

We have 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 the regulation: 

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. See the AD docket to examine 

the economic evaluation. 

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. 

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 

removing Amendment 39–13354 (68 FR 

61608; October 29, 2003), and adding 

the following new Airworthiness 

Directive (AD): 

2011–22–05 EUROCOPTER FRANCE 

(EUROCOPTER): Amendment 39–16847; 

Docket No. FAA–2011–1158; Directorate 

Identifier 2010–SW–018–AD; supersedes 

AD 2003–22–06, issued October 22, 2003 

(68 FR 61608; October 29, 2003), 

Amendment 39–13354, Docket No. 

2000–SW–12–AD. 

Applicability: Eurocopter Model AS350B, 

B1, B2, B3, BA, C, D, D1; and Model AS355E, 

F, F1, F2, N, and NP helicopters; with tail 

rotor (T/R) pitch control rod (control rod), 

part number (P/N) 350A33–2100–00, –01, 

–02, –03, –04; P/N 350A33–2121–00, –01, 

–02; P/N 350A33–2143–00; or P/N 350A33– 

2145–00 or –01, installed; certificated in any 

category. 

Compliance: Required as indicated. 

To prevent failure of a T/R control rod, loss 

of T/R control, and subsequent loss of control 

of the helicopter, accomplish the following: 

(a) Before the first flight of each day, place 

the T/R pedals in the neutral position. If the 

helicopter is fitted with a T/R load 

compensator, discharge the accumulator as 

described in the rotorcraft flight manual. 

Check the control rod bearing (bearing) for 

play on the helicopter, by observation and 

feel, by slightly moving the T/R blade in the 

flapping axis while monitoring the bearing 

for movement. See the following Figure 1 of 

this AD. The actions required by this 

paragraph may be performed by the owner/ 

operator (pilot) holding at least a private pilot 

certificate, and must be entered into the 

helicopter maintenance records showing 

compliance with this AD in accordance with 

14 CFR 43.9(a)(1)–(4) and 14 CFR 

91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.173, 

121.380, or 135.439. 

BILLING CODE 4910–13–P 


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(b) If the Teflon cloth is coming out of its 

normal position within the bearing, totally or 

partially, or if there is discoloration or 

scoring on the bearing, before further flight, 

replace the control rod with an airworthy 

control rod. 

(c) If a pilot or mechanic detects play, a 

mechanic must remove the control rod from 

the helicopter, and using a dial indicator, 

measure the bearing wear according to the 

following and as shown in Figures 2 and 3 

of this AD: 


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BILLING CODE 4910–13–C 

(1) Remove the control rod from the 

helicopter. 

(2) Mount the control rod in a vise as 

shown in Figure 2 of this AD. 

(3) Using a dial indicator, take axial play 

readings by moving the spherical bearing in 

the direction F (up and down) as shown in 

Figure 2 of this AD. 

(4) Install a bolt through the bearing and 

secure it with a washer and nut to provide 

a clamping surface when the bearing is 

clamped in a vise. 

(5) Mount the control rod and bearing in 

a vise as shown in Figure 3 of this AD. 

(6) Using a dial indicator, take radial play 

measurements by moving the control rod in 

the direction F as shown in Figure 3 of this 

AD. 

(7) Record the hours of operation on each 

control rod. 

(8) If the radial play exceeds 0.008 inch or 

axial play exceeds 0.016 inch, replace the 

control rod with an airworthy control rod 

before further flight. 

(9) If the radial and axial play are within 

limits, reinstall the control rod. 

(10) Thereafter, at intervals not to exceed 

30 hours time-in-service, remove the control 

rod and measure the bearing play with a dial 

indicator in accordance with paragraph (c) of 

this AD. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, DOT/FAA, ATTN: Jim 

Grigg, Manager, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5126, fax (817) 222– 

5961, for information about previously 

approved alternative methods of compliance. 

(e) The Joint Aircraft System/Component 

Code is 6720: Tail rotor control system. 

(f) This amendment becomes effective on 

November 25, 2011. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency (France) 

AD No. 2010–0006, dated January 7, 2010. 

Issued in Fort Worth, Texas, on October 12, 

2011. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27774 Filed 11–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0496; Airspace 

Docket No. 11–AWP–6] 

Establishment of Class D and 

Amendment of Class E Airspace; Los 

Angeles, CA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

D airspace at Los Angeles International 

Airport, Los Angeles, CA. Controlled 

airspace is necessary to contain 

potential missed approaches at Los 

Angeles International Airport. This 

action enhances the safety and 

management of aircraft operations at the 

airport. This action also edits Class E 

airspace by adding the geographic 

coordinates and the airport name to the 

airspace designation. 

DATES: Effective date, 0901 UTC, 

December 15, 2011. The Director of the 

Federal Register approves this 


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