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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42032 Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 

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 April 8, 2011 (76 FR 19721). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

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. It is 

possible that the fixation bracket assembly 

may be incorrectly orientated and as a result 

the position of the helicoil inserts on the 

fixation bracket may be incorrect. 

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. 

To address this potential unsafe condition, 

the TC [type certificate] holder has developed 

a one-time inspection to detect and correct 

any incorrect installations of the fixation 

brackets for rudder spring tabs and trim tabs. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed] 

inspection of all rudder trim- and spring tab 

fixation brackets, the correction of any parts 

that are incorrectly installed and the 

reporting of all findings to the TC holder. 

This [EASA] AD is considered to be an 

interim action and an improved design 

bracket attachment is expected to be 

developed. 

The detailed inspection includes 

determining if the helicoil inserts of the 

rudder trim tab and spring tab fixation 

brackets are correctly oriented and are 

facing the fitting surface, and if not, 

inspecting the fittings and helicoil 

inserts for correct installation. The 

corrective actions include re-orienting 

the fittings and helicoil inserts, and 

replacing the fitting with a serviceable 

one. 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 

about 55 products of U.S. registry. We 

also estimate that it will 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 to the U.S. operators to 

be $9,350, or $170 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: 

2011–15–07 328 Support Services GmbH 

(Type Certificate Previously Held by 

AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt 

GmbH): Amendment 39–16754. Docket 

No. FAA–2011–0308; Directorate 

Identifier 2010–NM–233–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH (Type Certificate previously 

held by AvCraft Aerospace GmbH; Fairchild 

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Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 42033 

Dornier GmbH; Dornier Luftfahrt GmbH) 

Model 328–100 and –300 airplanes, 

certificated in any category, all serial 

numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

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. 

* * * * * 

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. 

Inspection 

(g) Within 400 flight hours after the 

effective date of this AD, do a detailed 

inspection to determine if the fixation 

brackets for the rudder spring tabs and trim 

tabs are installed correctly, in accordance 

with the Accomplishment Instructions of 328 

Support Services Service Bulletin SB–328– 

55–493, dated April 21, 2010 (for Model 328– 

100 airplanes); or SB–328J–55–245, dated 

April 21, 2010 (for Model 328–300 airplanes). 

Corrective Action 

(h) If, during the inspection required by 

paragraph (g) of this AD, any incorrect 

installation of the fixation brackets for rudder 

spring tabs and trim tabs is detected, before 

further flight, correct the installation of the 

fixation brackets for rudder spring tabs and 

trim tabs, in accordance with the 

Accomplishment Instructions of 328 Support 

Services Service Bulletin SB–328–55–493, 

dated April 21, 2010 (for Model 328–100 

airplanes); or SB–328J–55–245, dated April 

21, 2010 (for Model 328–300 airplanes). 

Reporting 

(i) Within 30 days after the inspection 

required by paragraph (g) of this AD, or 

within 30 days after the effective date of this 

AD, whichever occurs later: Send the 

inspection report to 328 Support Services 

GmbH by using the Compliance Report 

attached to 328 Support Services Service 

Bulletin SB–328–55–493, dated April 21, 

2010 (for Model 328–100 airplanes); or SB– 

328J–55–245, dated April 21, 2010 (for Model 

328–300 airplanes). Send the report by mail 

or fax to: Attention: Dept. C, 328 Support 

Services GmbH, Customer Services, P.O. Box 

1252, D–82231 Wessling, Federal Republic of 

Germany; fax +49 (0) 8153 88111–6565. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) 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: 

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-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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

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

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0134, dated June 30, 2010; 

and 328 Support Services Service Bulletins 

SB–328–55–493 and SB–328J–55–245, both 

dated April 21, 2010; for related information. 

Material Incorporated by Reference 

(l) You must use 328 Support Services 

Service Bulletin SB–328–55–493, dated April 

21, 2010, including Compliance Report; or 

328 Support Services Service Bulletin SB– 

328J–55–245, dated April 21, 2010, including 

Compliance Report; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. Only the even pages of 

these documents include the document date. 

The compliance reports attached to these 

documents do not contain document 

numbers, revision levels, or dates. 

(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 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, 

D–82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(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. 2011–17703 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–2011–0718; Directorate 

Identifier 2011–NM–117–AD; Amendment 

39–16756; AD 2011–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

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 that would 

mstockstill on DSK4VPTVN1PROD with RULES