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. 


srobinson on DSK4SPTVN1PROD with 
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1727 

For service information identified in 

this AD, contact Grob Aircraft AG, 

Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Germany; 

phone: +49 (0) 8268 998 139; fax: +49 

(0) 8268 998 200; email: 

productsupport@grob-aircraft.com; 

Internet: www.grob-aircraft.com/ 

62.html. You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: 

jim.rutherford@faa.gov. 

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. That 

NPRM was published in the Federal 

Register on October 22, 2012 (77 FR 

64437). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Corroded and cracked elevator control road 

in the vertical fin on a Grob G 109B powered 

sailplane has been reported. 

The technical investigation revealed that 

water had soaked into the elevator control 

rod through a control bore hole and resulted 

in corrosion damage and, in case of water 

freeze between the external control rod and 

the internal mass balance, in crack of the 

elevator control rod in the vertical fin. 

This condition, if not detected and 

corrected, could lead to failure of the elevator 

control rod, possibly resulting in loss of 

control of the sailplane. 

To address this unsafe condition, Grob 

Aircraft AG published Service Bulletin 

(MSB) 817–64 providing instructions for 

elevator control rod inspection and 

replacement. 

For the reasons described above, this AD 

requires accomplishment of inspections of 

the elevator control rod in the vertical fin 

and, depending on finding, its replacement 

with a serviceable part, as well as a revision 

of powered sailplane Aircraft Maintenance 

Manual (AMM). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 64437, October 22, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the 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 (77 FR 

64437, October 22, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 64437, 

October 22, 2012). 

Costs of Compliance 

For Model G109 Sailplanes 

We estimate that this AD will affect 

31 products of U.S. registry. We also 

estimate that it would take about 2 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $5,270, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $680, for a cost of $765 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

For Model G109B Sailplanes 

We estimate that this AD will affect 

28 products of U.S. registry. We also 

estimate that it would take about 3.5 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $78 per 

product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $10,514, or $375.50 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $738, for a cost of $823 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 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; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM (77 FR 

64437, October 22, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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. 


srobinson on DSK4SPTVN1PROD with 
1728 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–26–09 Burkhart Grob Luft-Und: 

Amendment 39–17304; Docket No. 

FAA–2012–1124; Directorate Identifier 

2012–CE–041–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 13, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Burkhart GROB Luftund Raumfahrt GmbH Models GROB G 109 

and GROB G 109B sailplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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. 

We are issuing this AD to detect and correct 

corrosion and/or cracking of the elevator 

control rod, which could lead to failure of the 

elevator control rod with consequent loss of 

control. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) Within the next 25 hours time-inservice (TIS) after February 13, 2013 (the 

effective date of this AD) or within the next 

60 days after February 13, 2013 (the effective 

date of this AD), whichever occurs first, and 

repetitively thereafter at intervals not to 

exceed every 5 years, inspect the elevator 

control rod in the vertical fin for corrosion 

or cracking following the accomplishment 

instructions in Grob Aircraft AG Service 

Bulletin No. MSB817–64/2, dated September 

6, 2012. 

(2) For the purposes of this AD, we define 

slight corrosion as corrosion you can remove 

with metal wool and that has no visible 

pitting in the base metal. If you cannot 

remove the corrosion with metal wool or if 

there is visible pitting in the base metal, we 

define it as heavy corrosion. 

(3) If any cracks or heavy corrosion are 

found during any of the inspections required 

in paragraph (f)(1) of this AD, before further 

flight, replace the elevator control rod with 

an airworthy part following the 

accomplishment instructions in Grob Aircraft 

AG Service Bulletin No. MSB817–64/2, dated 

September 6, 2012, for your applicable 

sailplane model. 

(4) If only slight or no corrosion of the 

elevator control rod is found during any of 

the inspections required in paragraph (f)(1) of 

this AD, before further flight, clean the rod 

surface and apply a corrosion inhibitor, as 

applicable, following the accomplishment 

instructions in Grob Aircraft AG Service 

Bulletin No. MSB817–64/2, dated September 

6, 2012. 

Note 1 to paragraph (f) of this AD: Grob 

Aircraft AG incorporated the repetitive 

inspections required by this AD into the 

instructions for continued airworthiness of 

the aircraft maintenance manual for the 

applicable sailplanes. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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: For any 

reporting requirement in this AD, 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. 

(h) Related Information 

Refer to European Aviation Safety Agency 

(EASA), which is the Technical Agent for the 

Member States of the European Community, 

AD No.: 2012–0181, dated September 7, 

2012; and Grob Aircraft AG Service Bulletin 

No. MSB817–64/2, dated September 6, 2012, 

for related information. 

(i) 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) Grob Aircraft AG Service Bulletin No. 

MSB817–64/2, dated September 6, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Grob Aircraft AG, 

Lettenbachstrasse 9, D–86874 TussenhausenMattsies, Germany; phone: +49 (0) 8268 998 

139; fax: +49 (0) 8268 998 200; email: 

productsupport@grob-aircraft.com; Internet: 

www.grob-aircraft.com/62.html. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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/ 

index.html. 

Issued in Kansas City, Missouri, on 

December 21, 2012. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–31364 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–2012–0885; Directorate 

Identifier 2012–NE–18–AD; Amendment 39– 

17307; AD 2012–26–12] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Thielert Aircraft Engines GmbH (TAE) 

TAE 125–02–99 and TAE 125–02–114 

reciprocating engines. This AD requires 

inspection of the oil filler plug vent hole 

at the next scheduled maintenance or 

within 110 flight hours after the 

effective date of this AD. If chips are 

found to be blocking the vent hole, 

additional corrective action is required 

before next flight. This AD was 

prompted by an in-flight shutdown of 

an airplane equipped with a TAE 125– 

02–99 engine. We are issuing this AD to 

prevent engine in-flight shutdown or 

power loss, possibly resulting in 

reduced control of the airplane. 


srobinson on DSK4SPTVN1PROD with