Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 42029 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items ........ Revision 00 ........................... February 28, 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 7 .................................. December 2005. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 08 ................................ March 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 09 ................................ November 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 10 ................................ October 2009. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 11 ................................ September 2010. 

The issue level of Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 10, 

dated October 2009; and Issue 11, dated 

September 2010; is indicated only on the title 

page and in the Record of Revisions of these 

documents. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009; and Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 11, 

dated September 2010; under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in table 3 of this AD on November 

7, 2007 (72 FR 56262, October 3, 2007). 

TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Document Revision Date 

Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items ........ Revision 00 ........................... February 28, 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 7 .................................. December 2005. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 08 ................................ March 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 

95A.0252/96.

Issue 09 ................................ November 2006. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(4) 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. 

(5) 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 June 24, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–16559 Filed 7–15–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0309; Directorate 

Identifier 2010–NM–255–AD; Amendment 

39–16755; AD 2011–15–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model A300 C4– 

605R Variant F Airplanes (Collectively 

Called A300–600 Series Airplanes); 

and Model A310 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: 

A specific failure case of the THSA 

[trimmable horizontal stabilizer actuator] 

upper primary attachment, which may result 

in a loading of the upper secondary 

attachment, has been identified by analysis. 

Primary load path failure can be caused by 

bearing migration from the upper attachment 

gimbal by failure or loss of a retention bolt. 

In case of failure of the THSA upper 

primary attachment, the THSA upper 

secondary attachment would engage. Because 

the upper attachment secondary load path 

can only withstand the loads for a limited 

period of time, the condition where it would 

be engaged could lead, if not detected, to the 

failure of the secondary load path, which 

would likely result in loss of control of the 

aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 22, 2011. 

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42030 Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 

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 April 8, 2011 (76 FR 19724). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A specific failure case of the THSA 

[trimmable horizontal stabilizer actuator] 

upper primary attachment, which may result 

in a loading of the upper secondary 

attachment, has been identified by analysis. 

Primary load path failure can be caused by 

bearing migration from the upper attachment 

gimbal by failure or loss of a retention bolt. 

In case of failure of the THSA upper 

primary attachment, the THSA upper 

secondary attachment would engage. Because 

the upper attachment secondary load path 

can only withstand the loads for a limited 

period of time, the condition where it would 

be engaged could lead, if not detected, to the 

failure of the secondary load path, which 

would likely result in loss of control of the 

aeroplane. 

For the reasons explained above, this 

[EASA] AD requires installation of three 

secondary retention plates for the gimbal 

bearings on the THSA upper primary 

attachment. 

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 

215 products of U.S. registry. We also 

estimate that it will take about 4 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 $3,021 

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 

$722,615, or $3,361 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: 

2011–15–08 Airbus: Amendment 39–16755. 

Docket No. FAA–2011–0309; Directorate 

Identifier 2010–NM–255–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

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

airplanes, Model A300 B4–605R and B4– 

622R airplanes, Model A300 F4–605R and 

F4–622R airplanes, and Model A300 C4– 

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Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 42031 

605R Variant F airplanes; and Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A specific failure case of the THSA 

[trimmable horizontal stabilizer actuator] 

upper primary attachment, which may result 

in a loading of the upper secondary 

attachment, has been identified by analysis. 

Primary load path failure can be caused by 

bearing migration from the upper attachment 

gimbal by failure or loss of a retention bolt. 

In case of failure of the THSA upper 

primary attachment, the THSA upper 

secondary attachment would engage. Because 

the upper attachment secondary load path 

can only withstand the loads for a limited 

period of time, the condition where it would 

be engaged could lead, if not detected, to the 

failure of the secondary load path, which 

would likely result in loss of control 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 

(g) Within 30 months after the effective 

date of this AD, install three retention plates 

on the THSA upper primary attachment, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–27–6066 (for Model A300–600 

series airplanes) or Airbus Mandatory 

Service Bulletin A310–27–2103 (for Model 

A310 series airplanes), both dated June 10, 

2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) 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 FAAapproved 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 

(i) Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0224, dated November 4, 2010; and 

Airbus Mandatory Service Bulletins A300– 

27–6066 and A310–27–2103, both dated June 

10, 2010. 

Material Incorporated by Reference 

(j) You must use Airbus Mandatory Service 

Bulletin A300–27–6066, dated June 10, 2010; 

or Airbus Mandatory Service Bulletin A310– 

27–2103, dated June 10, 2010; as applicable; 

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 July 6, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17698 Filed 7–15–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0308; Directorate 

Identifier 2010–NM–233–AD; Amendment 

39–16754; AD 2011–15–07] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and –300 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: 

During maintenance, it has been 

discovered that at the installation of the 

fixation brackets for rudder spring tabs and 

trim tabs an incorrect installation of the 

fixation brackets may have occurred. * * * 

If the orientation of the fixation bracket is 

reversed or upside down the screws may not 

reach into the helicoil thread to a sufficient 

depth. 

An incorrect installation, if not detected 

and corrected, could lead to an in-flight 

failure of the fixation brackets for rudder 

spring tabs and trim tabs resulting in and 

reduced control of the aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 22, 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

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