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 


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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27243 

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]. 

For the reasons stated above, this [EASA] 

AD requires the replacement of bushes in the 

hydraulic reservoir panel. 

You may obtain further information 

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 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 our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

120 products of U.S. registry. We also 

estimate that it will take about 13 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $266 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $164,520, or 

$1,371 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will 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: 

2011–10–10 Airbus: Amendment 39–16691. 

Docket No. FAA–2011–0037; Directorate 

Identifier 2010–NM–273–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F airplanes, certificated in any 

category, all certified models, all serial 

numbers, except airplanes on which Airbus 

Mandatory Service Bulletin A300–24–6102 

(Airbus Modification 13381) has been 

embodied. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (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 

* * * 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 


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27244 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

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]. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 months after the effective 

date of this AD, install Teflon bushes in the 

hydraulic reservoir panel at the lower lefthand side in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before the effective date 

of this AD in accordance with Airbus 

Mandatory Service Bulletin A300–24–6102, 

dated August 13, 2009, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

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. Information may be e-mailed to: 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0225, 

dated November 5, 2010; and Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A300–24–6102, Revision 01, 

dated September 24, 2010, 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 Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 26, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10817 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–2010–0706; Directorate 

Identifier 2010–NM–064–AD; Amendment 

39–16683; AD 2011–10–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–400, 747–400D, 

and 747–400F Series Airplanes 

Equipped With General Electric CF6– 

80C2 or Pratt & Whitney PW4000 

Series Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

modifying certain thrust reverser control 

system wiring to the flap control unit 

(FCU). This AD was prompted by a 

report of automatic retraction of the 

leading edge flaps due to indications 

transmitted to the FCU from the thrust 

reverser control system during takeoff. 

We are issuing this AD to prevent 

automatic retraction of the leading edge 

flaps during takeoff, which could result 

in reduced climb performance and 

consequent collision with terrain and 

obstacles or forced landing of the 

airplane. 

DATES: This AD is effective June 15, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 15, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6505; fax 425–917–6590; e-mail: 

tung.tran@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 


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