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 
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1729 

DATES: This AD becomes effective 

February 13, 2013. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

February 13, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; email: frederick.zink@faa.gov; 

telephone: 781–238–7779; fax: 781– 

238–7199. 

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 August 31, 2012 (77 FR 

53154). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An engine in-flight shutdown has been 

reported on an aeroplane equipped with a 

TAE 125–02–99 engine. The results of the 

investigation showed that this was due to 

blockage of the gearbox oil filling plug vent 

hole, which caused pressurisation in the 

gearbox, resulting in oil leakage and a 

slipping clutch. This condition, if not 

corrected, could result in further cases of 

engine in-flight shutdown and consequent 

loss of control of the aeroplane. 

Further investigation revealed that the 

blockage to the oil cap vent was the 

result of a residual chip from machining 

the oil cap vent hole. The chip is from 

the manufacturing process and did not 

fall off the oil plug. This is not the result 

of material in the oil system causing the 

blockage. You may obtain further 

information including the affected 

gearbox serial number list by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 45 engines installed on airplanes 

of U.S. registry. We also estimate that it 

will take about 2.5 hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per hour. 

Required parts will cost about $30 per 

engine. Based on these figures, we 

estimate the cost of the AD to U.S. 

operators to be $10,913. 

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); and 

3. 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 AD and placed it in the AD docket. 

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 provided 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–26–12 Thielert Aircraft Engines 

GmbH: Amendment 39–17307; Docket 

No. FAA–2012–0885; Directorate 

Identifier 2012–NE–18–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 13, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Thielert Aircraft 

Engines (TAE) TAE 125–02–99 and TAE 

125–02–114 reciprocating engines. 

(d) Reason 

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. 

(e) Actions and Compliance 

Unless already done, within 110 flight 

hours after the effective date of this AD, or 

at the next scheduled maintenance, 

whichever occurs first, do the following. 

(1) Remove the oil filler plug and check for 

chips blocking the vent hole in accordance 

with TAE Service Bulletin (SB) TM TAE 

125–1015 P1, Initial Issue, dated April 27, 

2012. 

(2) If chips are found during the inspection 

in paragraph (e)(1) of this AD, disassemble 

the gearbox and check the radial shaft sealing 

rings (at the clutch and the propeller shaft) 

for leakage. If leakage is noted, replace the 

gearbox before the next flight. 


srobinson on DSK4SPTVN1PROD with 
1730 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install a gearbox with a S/N listed in TAE SB 

TM TAE 125–1015 P1, Initial Issue, dated 

April 27, 2012, into any engine unless the oil 

filler plug has passed the inspection required 

by paragraph (e)(1) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19. 

(h) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: frederick.zink@faa.gov; telephone 

(781) 238–7779; fax (781) 238–7199. 

(2) Refer to MCAI Airworthiness Directive 

No. 2012–0112, dated June 22, 2012, and 

TAE SB TM TAE 125–1015 P1, Initial Issue, 

dated April 27, 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) Thielert Aircraft Engines GmbH (TAE) 

Service Bulletin TM TAE 125–1015 P1, 

Initial Issue, dated April 27, 2012. 

(ii) Reserved. 

(3) For TAE service information identified 

in this AD, contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696–2912; 

email: info@centurion-engines.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

December 27, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–31589 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–2012–0601; Directorate 

Identifier 2008–SW–033–AD; Amendment 

39–17306; AD 2012–26–11] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Inc. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the Bell 

Helicopter Textron Inc. (BHTI) Model 

205A, 205A–1, and 205B helicopters 

with certain starter/generator power 

cable assemblies (power cable 

assemblies). This AD requires replacing 

the power cable assemblies and their 

associated parts, and performing 

continuity readings. This AD was 

prompted by the determination that the 

power cable assembly connector 

(connector) can deteriorate, causing a 

short in the connector that may lead to 

a fire in the starter/generator, smoke in 

the cockpit that reduces visibility, and 

subsequent loss of helicopter control. 

DATES: This AD is effective February 13, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 13, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth Texas 

76137. 

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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Andy Shaw, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, TX 76137; telephone (817) 

222–5110; email andy.shaw@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 13, 2012, at 77 FR 35306, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

BHTI Model 205A, 205A–1, and 205B 

helicopters with power cable 

assemblies, part numbers (P/N) 205– 

075–902–017 and P/N 205–075–911– 

007, installed. That NPRM proposed to 

require replacing the power cable 

assemblies and their associated parts, 

and performing continuity readings. The 

proposed requirements were intended to 

prevent a short in the connector that 

may lead to a fire in the starter/ 

generator, smoke in the cockpit that 

reduces visibility, and subsequent loss 

of helicopter control. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(77 FR 35306, June 13, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

We have reviewed BHTI Alert Service 

Bulletin (ASB) No. 205–07–94, Revision 

A, dated December 8, 2008, for Model 

205A and 205A–1 helicopters; and BHTI 

ASB No. 205B–08–50, dated December 

8, 2008, for the Model 205B helicopter. 

These ASBs describe procedures for 

replacing the power cable assemblies 

and associated parts. The ASBs specify 

that operators can obtain a starter/ 

generator cable kit that contains the 

required replacement parts. 

Costs of Compliance 

We estimate that this AD will affect 

31 helicopters of U.S. registry. The 

actions will take about 10 work-hours 

per helicopter to accomplish at an 

average labor rate of $85 per work hour. 

Required parts will cost about $12,654 


srobinson on DSK4SPTVN1PROD with