27240 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0127; Directorate 

Identifier 2010–CE–065–AD; Amendment 

39–16681; AD 2011–09–19] 

RIN 2120–AA64 

Airworthiness Directives; BURKHART 

GROB LUFT-UND Model G 103 C Twin 

III SL Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

15, 2011. 

On June 15, 2011, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

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. 

For service information identified in 

this AD, contact GROB Aircraft AG, 

Lettenbachstrasse 9, 86874 

Tussenhausen-Mattsies, Head of 

Customer Service and Support, 

Germany; telephone: +49 (0) 8268–998– 

139; fax: +49 (0) 8268–998–200; e-mail 

productsupport@grob-aircraft.com; 

Internet: http://www.grob-aircraft.eu. 

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. 

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 February 18, 2011 (76 FR 

9513). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

For the reasons stated above, this AD 

requires to inspect the propeller assembly 

attachment, to verify that the propeller track 

is within the allowable tolerances and, 

depending on findings, to accomplish the 

relevant corrective actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 4 

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 this AD on U.S. operators to 

be $680, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $100, for a cost of $610 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27241 

(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 Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains the NPRM, 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–09–19 BURKHART GROB LUFTUND: Amendment 39–16681; Docket No. 

FAA–2011–0127; Directorate Identifier 

2010–CE–065–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BURKHART GROB 

LUFT-UND G 103 C Twin III SL gliders, all 

serial numbers, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 61: Propellers/Propulsors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

For the reasons stated above, this AD 

requires to inspect the propeller assembly 

attachment, to verify that the propeller track 

is within the allowable tolerances and, 

depending on findings, to accomplish the 

relevant corrective actions. 

Actions and Compliance 

(f) Unless already done, within 30 days 

after the effective date of this AD, do the 

following actions: 

(1) Update the glider documentation 

following Grob Aircraft Service Bulletin No. 

MSB–869–24/1, dated July 20, 2009, by 

inserting the following revised pages from 

Grob Aircraft AG: 

(i) Into the Grob Aircraft AG G 103 C Twin 

III SL Pilot’s Operating Handbook (POH) 

(dated December 1991): Pages 0.2A, 0.3, 0.4, 

and 4.9, Revision 6, dated July 20, 2009. 

(ii) Into the Grob Aircraft AG G 103 C Twin 

III SL Maintenance Manual (dated December, 

1991) or FAA-approved maintenance 

program: pages 0.1A, 0.2, 0.3, 4.2, and 6.6, 

Revision 10, dated December 15, 2006. 

(2) Inspect for cracks at the bent area of the 

engaged tooth of the upper pulley wheel 

securing plate following the procedure to 

access the area found on page 6.12 of the 

Grob Aircraft AG G 103 C TWIN III SL 

Maintenance Manual, Date of Issue 

December, 1991, Revision 9, dated May 24, 

2002, as specified in Grob Aircraft Service 

Letter SL 869–01, dated June 9, 2009. 

(3) Verify that the propeller track (the play 

at the propeller tip) is within the allowable 

tolerances following the procedure on page 

4.9 of the Grob Aircraft AG G 103 C TWIN 

III SL POH, Date of Issue December, 1991, 

Revision 6, dated July 20, 2009, as specified 

in Grob Aircraft Service Letter SL 869–01, 

dated June 9, 2009. 

Note 1: The torque values and tolerances 

of the upper pulley wheel grooved nut have 

been standardized in the POH and 

maintenance manual. 

(4) If the bent area of the engaged tooth of 

the upper pulley wheel securing plate has no 

crack found per the inspection of paragraph 

(f)(2) of this AD, but the propeller track value 

measured is not within the allowable 

tolerances per paragraph (f)(3) of this AD, 

before further flight, readjust the torque of 

the upper pulley wheel grooved nut using the 

updated aircraft technical documentation 

following the procedure on page 6.12 of the 

Grob Aircraft AG G 103 C TWIN III SL 

Maintenance Manual, Date of Issue 

December, 1991, Revision 9, dated May 24, 

2002, as specified in Grob Aircraft Service 

Letter SL 869–01, dated June 9, 2009. Ensure 

accordingly that the propeller track is within 

the allowable tolerances following the 

procedure on page 4.9 of the Grob Aircraft 

AG G 103 C TWIN III SL POH, Date of Issue 

December, 1991, Revision 6, dated July 20, 

2009, as specified in Grob Aircraft Service 

Letter SL 869–01, dated June 9, 2009. If the 

propeller track is out of the allowable 

tolerance, then contact GROB for further 

instructions. 

(5) If any crack is found in the bent area 

of the engaged tooth of the upper pulley 

wheel securing plate per the inspection in 

paragraph (f)(2) of this AD, before further 

flight, do the following actions: 

(i) Remove the upper pulley wheel grooved 

nut and then look at the securing plate to 

identify if other teeth are available to be bent 

to secure the grooved nut. Do not bend an 

already bent tooth. If all teeth of the securing 

plate are already bent, replace the securing 

plate with a serviceable one. 

(ii) Screw back the upper pulley wheel 

grooved nut (and its securing plate) and 

tighten it, applying the torque following page 

6.12 of the Grob Aircraft AG G 103 C TWIN 

III SL Maintenance Manual, Date of Issue 

December, 1991, Revision 9, dated May 24, 

2002, as specified in Grob Aircraft Service 

Letter SL 869–01, dated June 9, 2009. Ensure 

accordingly that the propeller track is within 

the allowable tolerances following the 

procedure on page 4.9 of the Grob Aircraft 

AG G 103 C TWIN III SL POH, Date of Issue 

December, 1991, Revision 6, dated July 20, 

2009, as specified in Grob Aircraft Service 

Letter SL 869–01, dated June 9, 2009. If the 

propeller track is out of the allowable 

tolerances, then contact GROB for further 

instructions. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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. 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 


srobinson on DSKHWCL6B1PROD with RULES
27242 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to the following documents for 

related information: 

(1) MCAI EASA AD No.: 2010–0107, dated 

June 11, 2010; 

(2) Grob Aircraft Service Bulletin MSB 

869–24/1, dated July 20, 2009; 

(3) Grob Aircraft Service Letter SL–869–01, 

dated June 9, 2009; 

(4) Grob Aircraft AG G 103 C Twin III SL 

Pilot’s Operating Handbook (POH) (dated 

December 1991), pages 0.2A, 0.3, 0.4, and 

4.9, Revision 6, dated July 20, 2009; and 

(5) Grob Aircraft AG G 103 C Twin III SL 

Maintenance Manual (dated December 1991), 

page 6.12, Revision 9, dated May 24, 2002; 

and pages 0.1A, 0.2, 0.3, 4.2, and 6.6, 

Revision 10, dated December 15, 2006. 

(i) For service information related to this 

AD, contact GROB Aircraft AG, 

Lettenbachstrasse 9, 86874 TussenhausenMattsies, Head of Customer Service and 

Support, Germany; telephone: +49 (0) 8268– 

998–139; fax: +49 (0) 8268–998–200; e-mail 

productsupport@grob-aircraft.com; Internet: 

http://www.grob-aircraft.eu. 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. 

Material Incorporated by Reference 

(i) You must use Grob Aircraft Service 

Bulletin No. MSB–869–24/1, dated July 20, 

2009; Grob Aircraft Service Letter SL–869– 

01, dated June 9, 2009; Grob Aircraft AG G 

103 C Twin III SL Pilot’s Operating 

Handbook (POH) (dated December 1991), 

pages 0.2A, 0.3, 0.4, and 4.9, Revision 6, 

dated July 20, 2009; and Grob Aircraft AG G 

103 C Twin III SL Maintenance Manual 

(dated December 1991), page 6.12, Revision 

9, dated May 24, 2002; and pages 0.1A, 0.2, 

0.3, 4.2, and 6.6, Revision 10, dated 

December 15, 2006; to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact GROB Aircraft AG, 

Lettenbachstrasse 9, 86874 TussenhausenMattsies, Head of Customer Service and 

Support, Germany; telephone: +49 (0) 8268– 

998–139; fax: +49 (0) 8268–998–200; e-mail 

productsupport@grob-aircraft.com; Internet: 

http://www.grob-aircraft.eu. 

(3) 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. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on April 

22, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10388 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0037; Directorate 

Identifier 2010–NM–273–AD; Amendment 

39–16691; AD 2011–10–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from 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: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01– 

L296, dated March 4th, 2002, and 04/00/02/ 

07/03–L024, dated February 3rd, 2003, the 

JAA [Joint Aviation Authorities] 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

* * * are required to conduct a design 

review against explosion risks. 

During improvement of the protection of 

fuel pump wiring against short-circuit by 

accomplishment of Airbus Service Bulletin 

(SB) A300–24–6094, a study led by the 

manufacturer concluded that the harness, 

installed through the wing panel needed to 

be protected to prevent possible damage in 

case of chafing which could potentially lead 

to short-circuit [and intermittent function or 

loss of the inner tank fuel pump. Loss of both 

inner tank fuel pumps could result in 

inability to use the remaining fuel supply in 

the inner tank. A short-circuit could also 

result in an ignition source in a flammable 

leakage zone]. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 15, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

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 February 7, 2011 (76 FR 

6581). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01– 

L296, dated March 4th, 2002, and 04/00/02/ 

07/03–L024, dated February 3rd, 2003, the 

JAA [Joint Aviation Authorities] 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

with either a passenger capacity of 30 or 

more, or a payload capacity of 3,402 kg 

(7,500 lb) or more, which have received their 

certification since January 1st, 1958, are 

required to conduct a design review against 

explosion risks. 

During improvement of the protection of 

fuel pump wiring against short-circuit by 


srobinson on DSKHWCL6B1PROD with RULES