Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1723 

the response to the avian PPD 

tuberculin. 

(iv) A captive cervid tested with the 

CCT test must be classified as a reactor 

if: 

(A) It has a response to the bovine 

PPD tuberculin that is greater than 2 

mm and that is at least 0.5 mm greater 

than the response to the avian PPD 

tuberculin; or 

(B) It has been classified as a suspect 

on two successive CCT tests. 

(C) Any exceptions to the reactor 

classification under the conditions in 

paragraph (b)(1)(iv) of this section must 

be justified by the testing veterinarian in 

writing and have the concurrence of the 

DTE. 

(2) Dual Path Platform (DPP®) test. (i) 

The DPP® test is a supplemental test 

that may only be used in order to retest 

captive cervids that have been classified 

as suspects after being tested with the 

CervidTB Stat-Pak® test. The DPP® test 

may not be used as a primary test. 

(ii) A captive cervid that has nonnegative test results to its first DPP® test 

must be classified as a suspect, unless 

the DTE determines, based on 

epidemiological evidence, that the 

captive cervid should be classified as a 

reactor. A captive cervid classified as a 

suspect on its first DPP® test may be 

retested using the DPP® test to evaluate 

a new blood sample drawn from the 

cervid no less than 30 days after this 

first DPP® test. 

(iii) A captive cervid that has nonnegative test results on two successive 

DPP® tests must be classified as a 

reactor. 

■ 5. Section 77.39 is amended as 

follows: 

■ a. By adding new paragraphs (a)(1)(iii) 

and (a)(1)(iv); 

■ b. In paragraph (a)(2), by removing the 

words ‘‘CCT test or the BTB test’’ and 

adding the words ‘‘CCT test, DPP® test, 

or the BTB test’’ in their place; 

■ c. By revising paragraph (e), 

introductory text; 

■ d. By revising paragraph (e)(3); 

■ e. By revising paragraph (f)(1); and 

■ f. In paragraph (f)(2), by adding the 

words ‘‘or the CervidTB Stat-Pak® test’’ 

after the words ‘‘SCT test’’. 

The revisions and additions read as 

follows: 

§ 77.39 Other interstate movements. 

(a) * * * 

(1) * * * 

(iii) A captive cervid classified as a 

suspect on the CervidTB Stat-Pak® test 

must be quarantined until it is 

slaughtered or retested using the DPP®

test and found negative for tuberculosis 

based on the DPP® test. 

(iv) A captive cervid classified as a 

suspect on an initial DPP® test must be 

slaughtered or otherwise must be 

quarantined until it is retested using the 

DPP® test. A captive cervid that has 

negative test results to this second DPP®

test may be released from quarantine. A 

captive cervid that has non-negative test 

results to this second DPP® test must be 

classified as a reactor and may only be 

moved in accordance with paragraph (b) 

of this section. 

* * * * * 

(e) Herds that have received captive 

cervids from an affected herd. If a herd 

has received captive cervids from an 

affected herd, the captive cervids from 

the affected herd of origin will be 

considered exposed to tuberculosis. The 

exposed captive cervids and the 

receiving herd must be quarantined. The 

exposed captive cervids must be 

slaughtered, necropsied, or tested with 

the SCT test by a veterinarian employed 

by the State in which the test is 

administered or employed by USDA, or 

tested with the CervidTB Stat-Pak® test. 

Any exposed captive cervid that 

responds to the SCT test must be 

classified as a reactor and must be 

inspected at slaughter or necropsied. 

Any exposed captive cervid that has 

non-negative test results to the 

CervidTB Stat-Pak® test must be 

classified as a reactor and must be 

inspected at slaughter or necropsied. 

Any exposed captive cervid that tests 

negative to the SCT or CervidTB StatPak® test will be considered as part of 

the affected herd of origin for purposes 

of testing, quarantine, and the five 

annual whole herd tests required for 

affected herds in paragraph (d) of this 

section. 

* * * * * 

(3) If all the exposed captive cervids 

test negative for tuberculosis, the 

receiving herd will be released from 

quarantine if it is given a whole herd 

test and is found negative for 

tuberculosis and will return to the herd 

classification in effect before the herd 

was quarantined. In addition, the 

receiving herd will must be retested 

with the SCT or CervidTB Stat-Pak® test 

1 year after release from quarantine in 

order for captive cervids from the herd 

to continue to be moved interstate. 

Supplemental diagnostic tests may be 

used if any captive cervids in the herd 

show a response to the SCT test or have 

non-negative test results to the 

CervidTB Stat-Pak® test. 

(f) * * * 

(1) If the herd is identified as the 

source of captive cervids having lesions 

of tuberculosis and M. bovis has been 

confirmed by bacterial isolation from 

the slaughter animal, all captive cervids 

in the herd that respond to the SCT 

must be classified as reactors. All 

captive cervids in the herd that respond 

to the CervidTB Stat-Pak® test must be 

classified as reactors. If none respond to 

the SCT test or have non-negative test 

results to the CervidTB Stat-Pak® test, 

the herd may be released from 

quarantine and will return to the herd 

classification status in effect before the 

herd was quarantined, unless the DTE 

determines that additional testing is 

appropriate to ensure the herd’s 

freedom from tuberculosis. 

* * * * * 

Done in Washington, DC, this 2nd day of 

January 2013. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2013–00208 Filed 1–8–13; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1314; Directorate 

Identifier 2012–NM–227–AD; Amendment 

39–17312; AD 2012–26–51] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This emergency 

AD was sent previously to all known 

U.S. owners and operators of these 

airplanes. This AD requires revising the 

airplane flight manual (AFM) to advise 

the flight crew of emergency procedures 

for addressing Angle of Attack (AoA) 

sensor blockage. This AD also provides 

for optional terminating action for the 

AFM revision, which involves replacing 

AoA sensor conic plates with AoA 

sensor flat plates. This AD was 

prompted by a report that an airplane 

equipped with AoA sensors installed 

with conic plates recently experienced 

blockage of all sensors during climb, 

leading to autopilot disconnection and 

activation of the alpha protection 

(Alpha Prot) when Mach number was 

increased. We are issuing this AD to 

prevent reduced control of the airplane. 

DATES: This AD is effective January 24, 

2013 to all persons except those persons 


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1724 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

to whom it was made immediately 

effective by Emergency AD 2012–26–51, 

issued on December 17, 2012, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in the 

AD as of January 24, 2013. 

We must receive comments on this 

AD by February 25, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will 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; phone: 425–227–1405; fax: 

425–227–1149; email: 

sanjay.ralhan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 17, 2012, we issued 

Emergency AD 2012–26–51, which 

requires revising the airplane flight 

manual (AFM) to advise the flight crew 

of emergency procedures for addressing 

AoA sensor blockage. This emergency 

AD also provides for optional 

terminating action for the AFM revision, 

which involves replacing AoA sensor 

conic plates with AoA sensor flat plates. 

This emergency AD was sent previously 

to all known U.S. owners and operators 

of these airplanes. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Emergency Airworthiness Directive 

2012–0264–E, dated December 17, 2012 

(referred to after this as the Mandatory 

Continuing Airworthiness Information 

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

condition for the specified products. 

EASA has advised that an Airbus 

Model A330 airplane equipped with 

AoA sensors installed with conic plates 

recently 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 subsequent 

analysis, it is suspected that these conic 

plates may have contributed to the 

event. Investigations are ongoing 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 

airplane that the flight crew might not 

be able 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 airplane. 

EASA also issued Emergency AD 

2012–0258–E, dated December 4, 2012, 

for Airbus Model A330 and A340 

airplanes to require an amendment of 

the AFM to ensure that flight crews 

apply the applicable emergency 

procedure. 

AoA sensor conic plates of similar 

design are also installed on Model A320 

series airplanes. Installation of these 

AoA sensor conic plates was required 

for Model A318, A319, A320, and A321 

series airplanes by EASA AD 2012– 

0236, dated November 9, 2012 

(corrected November 12, 2012). 

Subsequently, EASA issued AD 2012– 

0236R1, dated December 17, 2012, to 

remove the requirement to install AoA 

sensor conic plates. 

Relevant Service Information 

We reviewed Airbus A318/A319/ 

A320/A321 Temporary Revision TR286, 

Issue 1.0, dated December 17, 2012, to 

the Airbus A318/A319/A320/A321 

Airplane Flight Manual (AFM). The 

temporary revision provides 

information to advise the flight crew of 

emergency procedures for addressing 

AoA sensor blockage. 

FAA’s Determination 

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 referenced above. We are issuing 

this AD because we evaluated all 

pertinent information and determined 

the unsafe condition exists and is likely 

to exist or develop on other products of 

the same type design. 

AD Requirements 

This AD requires revising the 

Emergency Procedures section of the 

Airbus A318/A319/A320/A321 AFM to 

incorporate Airbus A318/A319/A320/ 

A321 Temporary Revision TR286, Issue 

1.0, dated December 17, 2012, to advise 

the flight crew of emergency procedures 

for addressing AOA sensor blockage. 

This AD also provides for optional 

terminating action for the AFM revision, 

which involves replacing AoA sensor 

conic plates with AoA sensor flat plates. 

Interim Action 

We consider this AD to be an interim 

measure to mitigate risks associated 

with the installation of AoA sensor 

conic plates. Further AD action might 

follow. 

Clarification of Service Information 

References 

In the ‘‘Relevant Service Information’’ 

section of this AD and paragraph (h) of 

this AD, we have clarified that Airbus 

A318/A319/A320/A321 Temporary 

Revision TR286, Issue 1.0, dated 

December 17, 2012, is to the Airbus 

A318/A319/A320/A321 Airplane Flight 

Manual (AFM). We had not specified 

‘‘to the Airbus A318/A319/A320/A321 

Airplane Flight Manual (AFM)’’ in those 

locations in the emergency AD. This 

change does not affect AD compliance. 

We have also included Airbus A318/ 

A319/A320/A321 Temporary Revision 

TR286, Issue 1.0, dated December 17, 

2012, to the Airbus A318/A319/A320/ 

A321 AFM in paragraph (l)(2) of this 

AD, which specifies references for 

related information. We had not listed 

the temporary revision in the 

corresponding paragraph of the 

emergency AD (paragraph (l)(3) of the 

emergency AD). This change does not 

affect AD compliance. 


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Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1725 

We incorrectly referred to a service 

bulletin number as ‘‘Airbus Mandatory 

Service Bulletin A320–32–1521, dated 

* * * ’’ in the ‘‘Differences Between 

the AD and the MCAI or Service 

Information’’ section in the preamble of 

the emergency AD. The correct service 

bulletin reference is ‘‘Airbus Mandatory 

Service Bulletin A320–34–1521, dated 

* * * ’’ That reference is correct in the 

regulatory section of the emergency AD. 

We have revised the ‘‘Differences 

Between the AD and the MCAI or 

Service Information’’ section of this AD 

accordingly. This change does not affect 

AD compliance. 

Differences Between the AD and the 

MCAI or Service Information 

The applicability of EASA Emergency 

AD 2012–0264–E, dated December 17, 

2012, is limited to airplanes having an 

AoA sensor conic plate installed either 

in production or in service. However, 

this emergency AD applies to all of the 

affected airplane models; and this AD 

prohibits installation of an AoA sensor 

conic plate in service as specified in 

Airbus Mandatory Service Bulletin 

A320–34–1521, dated May 7, 2012; and 

Revision 01, dated September 12, 2012; 

on any airplane as of the effective date 

of this AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because we received a report 

indicating that an airplane equipped 

with AoA sensors installed with conic 

plates recently experienced blockage of 

all sensors during climb, leading to 

autopilot disconnection and activation 

of the alpha protection (Alpha Prot) 

when Mach number was increased. This 

condition could result in reduced 

control of the airplane. Therefore, we 

find that notice and opportunity for 

prior public comment are impracticable 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2012–1314 and Directorate 

Identifier 2012–NM–227–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 we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 793 

airplanes of U.S. registry. (We have 

confirmed that at least 65 airplanes have 

the affected configuration; however, 

there could be as many as 100.) 

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 

AFM Revision (100 airplanes) ........................ 1 work-hour × $85 per hour = $85 ................. $0 $85 $8,500 

We have received no definitive data 

that would enable us to provide cost 

estimates for the optional terminating 

action specified in this AD. 

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 

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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–26–51 Airbus: Amendment 39–17312; 

Docket No. FAA–2012–1314; Directorate 

Identifier 2012–NM–227–AD. 

(a) Effective Date 

This AD is effective January 24, 2013 to all 

persons except those persons to whom it was 

made immediately effective by Emergency 

AD 2012–26–51, issued on December 17, 

2012, which contained the requirements of 

this amendment. 


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1726 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

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

certificated in any category, all serial 

numbers. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 34: Navigation. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that an airplane equipped with 

Angle of Attack (AoA) sensors (with conic 

plates installed) recently experienced 

blockage of all sensors during climb, leading 

to autopilot disconnection and activation of 

the alpha protection (Alpha Prot) when Mach 

number was increased. We are issuing this 

AD to prevent reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Airplane Flight Manual Revision 

For airplanes on which an AoA sensor 

conic plate is installed in production by 

Airbus modification 153213 or 153214, or inservice 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 the effective date 

of this AD, revise the Emergency Procedures 

of the Airbus A318/A319/A320/A321 

Airplane Flight Manual (AFM) by inserting 

Airbus A318/A319/A320/A321 Temporary 

Revision TR286, Issue 1.0, dated December 

17, 2012, to advise the flight crew 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 temporary 

revision may be removed. 

(h) Optional Terminating Action 

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, 

to the Airbus A318/A319/A320/A321 AFM, 

may be removed from the AFM. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, 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) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Branch, 

ANM–116, 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 manager of the International Branch, 

send it to the attention of the person 

identified in the Related Information section 

of this AD. Information may be emailed to: 

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

(2) 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. 

(l) Related Information 

(1) For further information about this AD, 

contact: Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–227–1405; fax: 425–227–1149; 

email: sanjay.ralhan@faa.gov. 

(2) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Emergency 

Airworthiness Directive 2012–0264–E, dated 

December 17, 2012; and Airbus A318/A319/ 

A320/A321 Temporary Revision TR286, 

Issue 1.0, dated December 17, 2012, to the 

Airbus A318/A319/A320/A321 AFM; for 

related information. 

(m) 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) Airbus A318/A319/A320/A321 

Temporary Revision TR286, Issue 1.0, dated 

December 17, 2012, to the Airbus A318/ 

A319/A320/A321 Airplane Flight Manual. 

(ii) Reserved. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EAS, 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. 

(4) You may view this 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. 

(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 

December 27, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–31683 Filed 1–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1124; Directorate 

Identifier 2012–CE–041–AD; Amendment 

39–17304; AD 2012–26–09] 

RIN 2120–AA64 

Airworthiness Directives; Burkhart 

GROB Luft- und Raumfahrt GmbH 

Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Burkhart GROB Luft- und Raumfahrt 

GmbH Models GROB G 109 and GROB 

G 109B sailplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as 

corrosion and/or cracking of the elevator 

control rod that could lead to failure of 

the elevator control rod with consequent 

loss of control. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective February 13, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 13, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 


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