25666 Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 

12,000 flight hours or 4,400 flight cycles, 

whichever occurs first. 

(1) At the latest of the times specified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. 

(i) Within 12,000 flight hours since the 

airplane’s first flight; or 

(ii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done as specified in maintenance 

review board report (MRBR) Task 274000–12; 

or 

(iii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done, as specified in Airbus 

Mandatory Service Bulletin A330–27–3179 

or Airbus Mandatory Service Bulletin A340– 

27–4175, as applicable. (These service 

bulletins specify testing in case of type II or 

type III findings). 

(2) Within 1,000 flight hours after the 

effective date of this AD, but without 

exceeding the latest of the times specified in 

paragraphs (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of 

this AD. 

(i) 16,000 flight hours since the airplane’s 

first flight. 

(ii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in MRBR task 274000– 

12. 

(iii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in Airbus Mandatory 

Service Bulletin A330–27–3179, or Airbus 

Mandatory Service Bulletin A340–27–4175, 

as applicable. (These service bulletins specify 

testing in case of type II or type III findings). 

(h) Replacement 

If the result from any test required by 

paragraph (g) of this AD is not correct, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3191, dated June 7, 2012; 

or Airbus Mandatory Service Bulletin A340– 

27–4186, dated June 7, 2012; as applicable: 

Before further flight, replace the THSA with 

a serviceable THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3191, 

dated June 7, 2012; or Airbus Mandatory 

Service Bulletin A340–27–4186, dated June 

7, 2012; as applicable. Replacement of a 

THSA, as required by this paragraph, with a 

THSA having P/N 47147–500 or P/N 47147– 

700, is not terminating action for the 

repetitive tests required by paragraph (g) of 

this AD. 

(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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0210, dated October 11, 2012, 

and the service bulletins specified in 

paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, 

for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3191, dated June 7, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–27–4186, dated June 7, 2012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

review copies of the 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. 

Issued in Renton, Washington, on April 23, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10366 Filed 5–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0360; Directorate 

Identifier 2013–NM–033–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

The existing AD currently requires 

revising the airplane flight manual 

(AFM) to advise the flightcrew of 

emergency procedures for addressing 

angle of attack (AoA) sensor blockage. 

The existing AD also provides for 

optional terminating action for the AFM 

revision, which involves replacing AoA 

sensor conic plates with AoA sensor flat 

plates. Since we issued that AD, we 

have determined that the replacement of 

AoA sensor conic plates is necessary to 

address the identified unsafe condition. 

This proposed AD would mandate the 

installation of AoA sensor flat plates 

and removal of the AFM revision. We 

are proposing this AD to prevent 

reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 17, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. You 

may review copies of the 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. 

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 proposed 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. Comments will 

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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 25667 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0360; Directorate Identifier 

2013–NM–033–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 we receive 

about this proposed AD. 

Discussion 

On December 27, 2012, we issued AD 

2012–26–51, Amendment 39–17312 (78 

FR 1723, January 9, 2013). That AD 

required actions intended to address an 

unsafe condition on all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. 

Since we issued AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, 

January 9, 2013), we have determined 

that the replacement of the AoA sensor 

conic plates with flat plates is necessary 

to address the identified unsafe 

condition. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2013– 

0022, dated February 1, 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: 

Recently, an Airbus A330 aeroplane 

equipped with Angle of Attack (AoA) sensors 

with conic plates installed, experienced 

blockage of all sensors during climb, leading 

to autopilot disconnection and activation of 

the alpha protection (Alpha Prot) when Mach 

number was increased. 

Based on the results of the subsequent 

analysis, it is suspected that these conic 

plates may have contributed to the event. 

Investigations are on-going to determine what 

caused the blockage of these AoA sensors. 

Blockage of two or three AoA sensors at the 

same angle may cause the Alpha Prot of the 

normal law to activate. Under normal flight 

conditions (in normal law), if the Alpha Prot 

activates and Mach number increases, the 

flight control laws order a pitch down of the 

aeroplane that the flight crew may be unable 

to counteract with a side stick deflection, 

even in the full backward position. 

This condition, if not corrected, could 

result in reduced control of the aeroplane. 

AoA conic plates of similar design are also 

installed on A320 family aeroplanes, and 

installation of these AoA sensor conic plates 

was required by EASA AD 2012–0236, 

making reference to Airbus Service Bulletin 

(SB) A320–34–1521 for in-service 

modification. 

That requirement was deleted by EASA AD 

2012–0236R1. 

To address this potential unsafe condition 

on A320 family aeroplanes, Airbus 

developed an ‘‘AOA Blocked’’ emergency 

procedure, published as a temporary revision 

(TR) of the Airplane Flight Manual (AFM), to 

ensure that flight crews, in case of AoA 

sensors blockage, apply the applicable 

emergency procedure. 

Consequently, EASA issued Emergency AD 

2012–0264–E [which corresponds to FAA AD 

2012–26–51, Amendment 39–17312 (78 FR 

1723, January 9, 2013)] to require amendment 

of the AFM by incorporating the Airbus TR. 

Since that [EASA] AD was issued, Airbus 

published approved instructions to re-install 

AoA sensor flat plates on A320 family 

aeroplanes. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0264–E which is superseded, and 

requires installation of AoA sensor flat 

plates, after which the AFM operational 

procedure can be removed. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

In AD 2012–26–51, Amendment 39– 

17312 (78 FR 1723, January 9, 2013), we 

determined that the AFM operational 

procedure specified in Airbus A318/ 

A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 

2012, mitigates risks associated with 

installation of conic plates. This 

proposed AD would require installation 

of flat plates to address the identified 

unsafe condition. After analysis of the 

safety benefit of the AFM operational 

procedure, we determined that the 

previously mandated AFM operational 

procedure must be removed after 

replacement of the conic plates with flat 

plates. 

Paragraph (h) of AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, 

January 9, 2013), only specifies that 

Airbus A318/A319/A320/A321 

Temporary Revision TR286, Issue 1.0, 

dated December 17, 2012, may be 

removed after accomplishing the 

modification (installation of flat plates). 

Therefore, we have revised paragraph 

(h) of this proposed AD to require that 

after the modification for an airplane 

has been done, Airbus A318/A319/ 

A320/A321 Temporary Revision TR286, 

Issue 1.0, dated December 17, 2012, 

must be removed before further flight. 

For airplanes on which the modification 

has already been done, we have allowed 

a compliance time of ‘‘within 5 days 

after the effective date of this AD’’ for 

accomplishing the removal. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–34–1564, including 

Appendix 01, dated January 25, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 100 products of U.S. 

registry. 

The actions that are required by AD 

2012–26–51, Amendment 39–17312 (78 

FR 1723, January 9, 2013), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $85 per 

product. 

We estimate that it would take about 

7 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. We have received no 

definitive data that would enable us to 

provide part cost estimates. Where the 

service information lists required parts 

costs that are covered under warranty, 

we have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

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25668 Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 

proposed AD on U.S. operators to be 

$59,500, or $595 per product. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed 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; 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 a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2012–26–51, Amendment 39–17312 (78 

FR 1723, January 9, 2013), and adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0360; 

Directorate Identifier 2013–NM–033–AD. 

(a) Comments Due Date 

We must receive comments by June 17, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013). 

(c) Applicability 

This AD applies to the Airbus airplanes 

listed in paragraphs (c)(1) through (c)(4) of 

this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by a determination 

that replacement of angle of attack (AoA) 

sensor conic plates is necessary to address 

the identified unsafe condition. We are 

issuing this AD to prevent reduced control of 

the airplane. 

(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) Retained Airplane Flight Manual 

Revision With New Exception 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013), with a new exception. Except as 

specified in paragraph (k) of this AD, for 

airplanes on which an AoA sensor conic 

plate is installed in production by Airbus 

modification 153213 or 153214, or in-service 

as specified in Airbus Mandatory Service 

Bulletin A320–34–1521, dated May 7, 2012; 

or Revision 01, dated September 12, 2012: 

Within 5 days after January 24, 2013 (the 

effective date of AD 2012–26–51), revise the 

Emergency Procedures of the Airbus A318/ 

A319/A320/A321 Airplane Flight Manual 

(AFM) by inserting Airbus A318/A319/A320/ 

A321 Temporary Revision (TR) TR286, Issue 

1.0, dated December 17, 2012, to advise the 

flightcrew of emergency procedures for 

addressing AoA sensor blockage. When the 

information in Airbus A318/A319/A320/ 

A321 Temporary Revision TR286, Issue 1.0, 

dated December 17, 2012, is included in the 

general revisions of the AFM, the general 

revisions may be inserted in the AFM, and 

the TR may be removed. Accomplishment of 

the new flat plate installation required by 

paragraph (j) of this AD terminates the 

actions required by this paragraph; and after 

the installation of new flat plates has been 

done, Airbus A318/A319/A320/A321 

Temporary Revision TR286, Issue 1.0, dated 

December 17, 2012, must be removed from 

the AFM before further flight. 

(h) Retained Optional Terminating Action 

With Revised TR Removal Requirement 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–26–51, 

Amendment 39–17312 (78 FR 1723, January 

9, 2013), with a revised TR removal 

requirement. Modification of an airplane by 

replacing AoA sensor conic plates with AoA 

sensor flat plates, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, constitutes 

terminating action for the AFM revision 

required by paragraph (g) of this AD; and 

after the modification has been done, Airbus 

A318/A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 2012, 

must be removed from the AFM before 

further flight, except for airplanes on which 

the modification has been done before the 

effective date of this AD. For airplanes on 

which the modification has been done before 

the effective date of this AD, Airbus A318/ 

A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 2012, 

must be removed from the AFM within 5 

days after the effective date of this AD. 

Accomplishment of the actions required by 

paragraphs (j) and (l) of this AD terminate the 

actions specified in this paragraph. 

(i) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–26–51, Amendment 

39–17312 (78 FR 1723, January 9, 2013). As 

of January 24, 2013 (the effective date of AD 

2012–26–51), no person may install an AoA 

sensor conic plate in service using Airbus 

Mandatory Service Bulletin A320–34–1521, 

dated May 7, 2012; or Revision 01, dated 

September 12, 2012; on any airplane. 

(j) New Flat Plate Installation 

Within 5 months after the effective date of 

this AD, remove all AoA sensor conic plates 

having part number (P/N) F3411060200000 

or P/N F3411060900000 and install AoA 

sensor flat plates having part numbers 

specified in paragraph (j)(1) or (j)(2) of this 

AD, except as specified in paragraph (k) of 

this AD. Install the AoA sensor plates in 

accordance with the applicable method 

specified in paragraph (j)(1) or (j)(2) of this 

AD. Accomplishment of the AoA sensor flat 

plate installation terminates the AFM 

revision required by paragraph (g) of this AD; 

and after accomplishing the installation, the 

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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 25669 

actions specified in paragraph (l) of this AD 

must be done. 

(1) Install P/N D3411013520200 in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–34–1564, including Appendix 

01, dated January 25, 2013. 

(2) Install P/N D3411007620000 or P/N 

D3411013520000, in accordance with 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). 

(k) New Exception to Paragraphs (g) and (j) 

of This AD 

An airplane on which Airbus modification 

154863 (installation of AOA sensor flat plate) 

and modification 154864 (coating protection) 

have been embodied in production is not 

affected by the requirements of paragraph (g) 

or (j) of this AD, provided that, since first 

flight, no AoA sensor conic plate having 

P/N F3411060200000 or P/N 

F3411060900000 has been installed on that 

airplane. 

(l) New Removal of AFM Revision 

After modification of an airplane as 

required by paragraph (j) of this AD, Airbus 

A318/A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 2012, 

that was inserted into the Airbus A318/A319/ 

A320/A321 AFM as required by paragraph (g) 

of this AD is no longer required and must be 

removed from the AFM of that airplane 

before further flight. 

(m) New Parts Installation Prohibition 

(1) As of the effective date of this AD, for 

any airplane that has AoA sensor flat plates 

installed: As of the effective date of this AD, 

do not install any AoA sensor conic plate 

having P/N F3411060200000 or P/N 

F3411060900000, and do not use any AoA 

protection cover having P/N 

98D34203003000. 

(2) For any airplane that has AoA sensor 

conic plates installed: As of the effective date 

of this AD, after modification of the airplane 

as required by paragraph (j) of this AD, do 

not install any AoA sensor conic plate having 

P/N F3411060200000 or P/N 

F3411060900000, and do not use any AoA 

protection cover having P/N 

98D34203003000. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199) to operate the airplane to a 

location where the airplane can be modified 

(if the operator elects to do so), provided 

Airbus A318/A319/A320/A321 Temporary 

Revision TR286, Issue 1.0, dated December 

17, 2012, has been inserted into the 

Emergency Procedures of the Airbus A318/ 

A319/A320/A321 AFM. 

(o) 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, WA 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0022, dated 

February 1, 2013; Airbus Mandatory Service 

Bulletin A320–34–1564, including Appendix 

01, dated January 25, 2013; and Airbus A318/ 

A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 2012. 

(2) 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the 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. 

Issued in Renton, Washington, on April 23, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10361 Filed 5–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF STATE 

22 CFR Part 62 

[Public Notice 8308] 

RIN 1400–AC60 

Exchange Visitor Program—Teachers 

AGENCY: Department of State. 

ACTION: Proposed rule with request for 

comment. 

SUMMARY: The Department is amending 

existing regulations governing the 

teacher category of the Exchange Visitor 

Program. The proposed amendments 

clarify the duration of program 

participation; amend eligibility 

requirements with respect to verifying 

English proficiency; and reduce the 

required teaching or related experience 

from three years to the equivalent of two 

years full-time teaching experience; 

introduce a required cultural 

component; and propose the 

implementation of a two-year bar for 

repeat participation to foster the 

purpose of the Mutual Educational and 

Cultural Exchange Act of 1961, 

(‘‘Fulbright-Hays Act’’). These proposed 

changes will enhance the integrity and 

programmatic effectiveness of the 

teacher category. 

DATES: The Department will accept 

comments on the proposed regulation 

from the public up to July 1, 2013. 

ADDRESSES: You may submit comments 

identified by any of the following 

methods: 

• Persons with access to the Internet 

may also view this notice and provide 

comments by going to the 

regulations.gov Web site at: http:// 

www.regulations.gov/index.cfm and 

searching for the RIN (1400–AC60) 

• Mail (paper, disk, or CD–ROM 

submissions): U.S. Department of State, 

Office of Private Sector Exchange, SA– 

5, Floor 5, 2200 C Street NW., 

Washington, DC 20522–0505. 

• Email: JExchanges@state.gov. You 

must include the RIN (1400–AC60) in 

the subject line of your message. 

FOR FURTHER INFORMATION CONTACT: 

Robin J. Lerner, Deputy Assistant 

Secretary for Private Sector Exchange, 

U.S. Department of State, SA–5, Floor 5, 

2200 C Street NW., Washington, DC 

20522–0505; telephone: (202) 632–2805; 

fax (202) 632–2701. 

SUMMARY: Statement of Need. In recent 

years, the teacher exchange program has 

been used by some sponsors in a 

manner that falls outside the original 

intent of the program. Occasionally, it 

has been used to fill a labor need in U.S. 

public and private schools rather than to 

further a cultural exchange. The 

Department has identified issues 

regarding job placements, wages and 

hours, and is of the opinion that the 

program lacks a cultural component 

necessary for the program to be 

consistent with the Mutual Educational 

and Cultural Exchange Act of 1961, as 

amended. In addition, the substance of 

this rule has been informed by analysis 

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