63156 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 

definition of ‘‘Qualified debt’’ in 

paragraph (g)(15), to read as follows: 

§ 120.882 Eligible Project costs for 504 

loans. 

* * * * * 

(e) * * * 

(1) Substantially all (85% or more) of 

the proceeds of the indebtedness were 

used to acquire land, including a 

building situated thereon, to construct a 

building thereon, or to purchase 

equipment. The assets acquired must be 

eligible for financing under the 504 loan 

program. If the acquisition, construction 

or purchase of the asset was originally 

financed through a commercial loan that 

would have satisfied the ‘‘substantially 

all’’ requirement and that was 

subsequently refinanced one or more 

times, with the current commercial loan 

being the most recent refinancing, the 

current commercial loan will be deemed 

to satisfy this paragraph (e)(1). 

* * * * * 

(g) * * * 

(4) In addition to the annual guarantee 

fee assessed under § 120.971(d)(2), 

Borrower must pay SBA a supplemental 

annual guarantee fee to cover the 

additional cost attributable to the 

refinancing in an amount established by 

SBA each fiscal year. 

(5) The funding for the Refinancing 

Project must come from three sources 

based on the current fair market value 

of the fixed assets serving as collateral 

for the Refinancing Project, including a 

Third Party Loan that is at least as much 

as the 504 loan, not less than 10% from 

the Borrower (excluding administrative 

costs), and not more than 40% from the 

504 loan. In addition to a cash 

contribution, the Borrower’s 10% 

contribution may be satisfied as set forth 

in § 120.910 or by the equity in any 

other fixed assets that are acceptable to 

SBA as collateral for the Refinancing 

Project, provided that there is an 

independent appraisal of the fair market 

value of the asset; 

(6)(i) The portion of the Refinancing 

Project provided by the 504 loan and the 

Third Party Loan may be no more than 

90% of the fair market value of the fixed 

assets that will serve as collateral; 

(ii) The Borrower’s application may 

include a request to finance eligible 

business expenses as part of the 

Refinancing Project if the amount of 

cash funds that will be provided for the 

Refinancing Project exceeds the amount 

to be paid to the lender of the Qualified 

Debt. The Borrower’s application must 

include a specific description of the 

business expenses for which the 

financing is requested and an 

itemization of the amount of each 

expense. For the purposes of this 

paragraph (b), ‘‘eligible business 

expenses’’ means the business expenses 

of the Borrower, such as salaries, rent, 

utilities, inventory, or other obligations 

of the business, that were incurred but 

not paid prior to the date of application 

or that will become due for payment 

within eighteen months after the date of 

application. Both the CDC and the 

Borrower must certify in the application 

that the funds will be used to cover 

eligible business expenses. Borrower 

must, upon request, substantiate the use 

of the funds provided for business 

expenses through, for example, bank 

statements, invoices marked ‘‘paid,’’ 

cleared checks, or any other documents 

that demonstrate that a business 

obligation was satisfied with the funds 

provided. 

* * * * * 

(15) * * * 

Qualified debt * * * 

(iii) Substantially all (85% or more) of 

which was for an Eligible Fixed Asset. 

If the Eligible Fixed Asset was originally 

financed through a commercial loan that 

would have satisfied the ‘‘substantially 

all’’ standard (the ‘‘original loan’’) and 

that was subsequently refinanced one or 

more times, with the current 

commercial loan being the most recent 

refinancing, the current commercial 

loan will be deemed to satisfy this 

paragraph (iii). If the original loan was 

for the construction of a new building, 

or the acquisition, renovation, or 

reconstruction of an existing building, 

and such loan would not have satisfied 

the leasing policies set forth in 13 CFR 

120.131 and 13 CFR 120.870(b), the 

current commercial loan will be deemed 

to satisfy these policies, provided that 

Borrower demonstrates compliance with 

13 CFR 120.131(b) for existing buildings 

as of the date of application. 

* * * * * 

(vii) For which the applicant for the 

refinancing available under this 

paragraph (g) has been current on all 

payments due for not less than one year 

preceding the date of application. For 

the purposes of this paragraph (vii), 

‘‘current on all payments due’’ means 

that no payment was more than 30 days 

past due from either the original 

payment terms or modified payment 

terms (including deferments) if such 

modification was agreed to in writing by 

the Borrower and the lender of the 

existing debt prior to the October 12, 

2011. Any delinquency in payment on 

the loan to be refinanced after approval 

and before debenture funding must be 

reported to SBA as an adverse change. 

* * * * * 

Karen G. Mills, 

Administrator. 

[FR Doc. 2011–26311 Filed 10–7–11; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0568; Directorate 

Identifier 2011–NM–010–AD; Amendment 

39–16824; AD 2011–21–01] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.27 Mark 050, 

200, 300, 400, 500, 600, and 700 

Airplanes; and Model F.28 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 Federal Aviation Administration 

(FAA) has published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) has published 

Interim Policy INT/POL/25/12. The review 

conducted by Fokker Services on the Fokker 

F27 and F28 type designs in response to 

these regulations revealed that, under certain 

failure conditions, a short circuit can develop 

in the fuel pilot valve solenoid or in the 

wiring to the solenoid. Such a short circuit 

may result in an ignition source in the wing 

tank vapour space. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 16, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

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Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 63157 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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 June 21, 2011 (76 FR 36011). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

[T]he Federal Aviation Administration 

(FAA) has published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) has published 

Interim Policy INT/POL/25/12. The review 

conducted by Fokker Services on the Fokker 

F27 and F28 type designs in response to 

these regulations revealed that, under certain 

failure conditions, a short circuit can develop 

in the fuel pilot valve solenoid or in the 

wiring to the solenoid. Such a short circuit 

may result in an ignition source in the wing 

tank vapour space. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this AD 

requires [re-working the wiring and] the 

installation of a fuse packed in a jiffy 

junction [i.e., crimped wire in-line junction 

device] in the wiring to the fuel pilot valve 

solenoid. 

The required actions also include 

revising the maintenance program to 

include a certain Critical Design 

Configuration Control Limitation 

(CDCCL). 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 (76 

FR 36011, June 21, 2011) 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 6 

products of U.S. registry. We also 

estimate that it will take about 6 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 up to $2,198 

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 up to 

$16,248, or up to $2,708 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 (76 FR 36011, June 

21, 2011), 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: 

2011–21–01 Fokker Services B.V.: 

Amendment 39–16824. Docket No. 

FAA–2011–0568; Directorate Identifier 

2011–NM–010–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 16, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.27 Mark 050, 200, 300, 400, 500, 

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63158 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 

600, and 700 airplanes; and Fokker Services 

B.V. Model F.28 Mark 0070, 0100, 1000, 

2000, 3000, and 4000 airplanes; certificated 

in any category; all serial numbers. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include a new Critical Design Configuration 

Control Limitation (CDCCL). Compliance 

with this CDCCL is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by this AD, the operator 

may not be able to accomplish the actions 

described in the revisions. In this situation, 

to comply with 14 CFR 91.403(c), the 

operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (j)(1) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[T]he Federal Aviation Administration 

(FAA) has published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) have published 

Interim Policy INT/POL/25/12. The review 

conducted by Fokker Services on the Fokker 

F27 and F28 type designs in response to 

these regulations revealed that, under certain 

failure conditions, a short circuit can develop 

in the fuel pilot valve solenoid or in the 

wiring to the solenoid. Such a short circuit 

may result in an ignition source in the wing 

tank vapour space. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

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. 

Installation of Fuses Packed in Jiffy 

Junctions 

(g) Within 24 months after the effective 

date of this AD, re-work the wiring and 

install the fuses packed in jiffy junctions (i.e., 

crimped wire in-line junction device), in 

accordance with the Accomplishment 

Instructions of the applicable Fokker service 

bulletin identified in table 1 of this AD. 

TABLE 1—SERVICE BULLETINS

Fokker Service Bulletin— Dated— 

SBF50–28–024, including Drawing W7916–057, Sheets 006 and 007, Issue E, dated June 23, 2010, Drawing W7987–520, 

Sheets 1 and 2, dated October 24, 2005, and Manual Change Notification—Maintenance Document MCNM–F50–070, dated 

June 23, 2010.

June 23, 2010. 

SBF28–28–051, including Drawing W57231, Sheets 010 and 011, Issue K, dated June 23, 2010, Drawing W58048, Sheet 2, 

dated April 29, 2010, and Manual Change Notification—Maintenance Document MCNM–F28–034, dated June 23, 2010.

June 23, 2010. 

SBF27–28–069, including Drawing W7202–138, Sheets 001 and 002, Issue B, dated June 23, 2010, and Manual Change Notification—Maintenance Document MCNM–F27–025, dated June 23, 2010.June 23, 2010. 

SBF100–28–042, including Drawing W41192, Sheet 012, Issue AG, dated June 23, 2010, Drawing W59520, Sheet 1, Issue A, 

dated April 29, 2010, and Manual Change Notification—Maintenance Document MCNM–F100–129, dated June 23, 2010.

June 23, 2010. 

Critical Design Configuration Control 

Limitation (CDCCL) 

(h) Before further flight after doing the 

actions required by paragraph (g) of this AD: 

Revise the aircraft maintenance program by 

incorporating the CDCCL specified in 

paragraph 1.L.(1)(c) of the applicable Fokker 

service bulletins identified in table 1 of this 

AD. 

No Alternative Actions, Intervals, and/or 

CDCCLs 

(i) After accomplishing the revision 

required by paragraph (h) of this AD, no 

alternative CDCCLs may be used unless the 

CDCCLs are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j)(1) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0195, dated September 29, 2010, 

specifies revising the maintenance program 

to include maintaining CDCCLs, this AD only 

requires the revision. Requiring a revision of 

the maintenance program, rather than 

requiring maintaining CDCCLs, requires 

operators to record AD compliance only at 

the time the revision is made. Maintaining 

CDCCLs specified in the airworthiness 

limitations must be complied with in 

accordance with 14 CFR 91.403(c). 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance: 

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: Tom Rodriguez, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone 425–227–1137; fax 

425–227–1149. Information may be e-mailed 

to: 9-ANM-11-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 

(k) Refer to MCAI EASA Airworthiness 

Directive 2010–0195, dated 

September 29, 2010, and the Fokker service 

bulletins identified in table 1 of this AD, for 

related information. 

Material Incorporated by Reference 

(l) You must use the following service 

information, as applicable, to do the actions 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference (IBR) under 5 U.S.C. 552(a) and 1 

CFR part 51 of the following service 

information on the date specified. 

(1) Fokker Service Bulletin SBF50–28–024, 

including Manual Change Notification— 

Maintenance Document MCNM–F50–070, 

dated June 23, 2010, and including Drawing 

W7916–057, Sheets 006 and 007, Issue E, 

dated June 23, 2010, and Drawing W7987– 

520, Sheets 1 and 2, dated October 24, 2005, 

approved for IBR November 16, 2011. 

(2) Fokker Service Bulletin SBF28–28–051, 

including Manual Change Notification— 

Maintenance Document MCNM–F28–034, 

dated June 23, 2010, and including Drawing 

W57231, Sheets 010 and 011, Issue K, dated 

June 23, 2010, and Drawing W58048, Sheet 

2, dated April 29, 2010, approved for IBR 

November 16, 2011. 

(3) Fokker Service Bulletin SBF27–28–069, 

including Manual Change Notification— 

Maintenance Document MCNM–F27–025, 

dated June 23, 2010, and including Drawing 

W7202–138, Sheets 001 and 002, Issue B, 

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dated June 23, 2010, approved for IBR 

November 16, 2011. 

(4) Fokker Service Bulletin SBF100–28– 

042, including Manual Change Notification— 

Maintenance Document MCNM–F100–129, 

dated June 23, 2010, and including Drawing 

W41192, Sheet 012, Issue AG, dated June 23, 

2010, and Drawing W59520, Sheet 1, Issue A, 

dated April 29, 2010, approved for IBR 

November 16, 2011. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet: http://www.myfokkerfleet.com. 

(6) 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. 

(7) 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 

September 23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25768 Filed 10–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0999; Directorate 

Identifier 2010–NM–235–AD; Amendment 

39–16825; AD 2011–21–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–243F Airplanes Equipped With 

Rolls Royce Trent 700 Series Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

During flight tests, unexpected fatigue high 

loads were measured on the hinges integrated 

on the 12 o’clock beam which form the upper 

extreme edge of the thrust reverser unit C 

duct. 

This situation, if not corrected, could lead 

to the separation of the thrust reverser from 

the aeroplane and therefore to damage of the 

aeroplane and hazards to persons or property 

on the ground. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

October 27, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 27, 2011. 

We must receive comments on this 

AD by November 28, 2011. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

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 (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0187, 

dated September 21, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During flight tests, unexpected fatigue high 

loads were measured on the hinges integrated 

on the 12 o’clock beam which form the upper 

extreme edge of the thrust reverser unit C 

duct. 

This situation, if not corrected, could lead 

to the separation of the thrust reverser from 

the aeroplane and therefore to damage of the 

aeroplane and hazards to persons or property 

on the ground. 

DGAC [Directorate General for Civil 

Aviation] AD F–1997–118–047 was issued to 

prevent structural damage of the thrust 

reversers. 

This [EASA] AD, which supersedes DGAC 

AD F–1997–118–047R2 [which corresponds 

with FAA AD 2001–09–14, Amendment 39– 

12221 (66 FR 23838, May 10, 2001] * * * is 

issued to extend the applicability to the 

newly certified model A330–243F. 

Required actions include repetitive 

general visual inspections for cracks of 

the hinge assemblies and along the 

beam structure of the right and left 

engine thrust reversers, detailed 

inspection for cracking of hinges 2, 3, 4, 

and 5 of the left and right thrust 

reversers if no cracking is found during 

any general inspection, and replacing 

the affected thrust reverser of each 

engine if any crack is found. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–78–3006, Revision 09, 

including Appendix 1, dated October 

21, 2009. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

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 and service information 

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. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

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