Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19721 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2011–0307; Directorate Identifier 

2010–NM–111–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A report has been received of an incident 

where one of the two bolts attaching the 

actuator mounting bracket to the MLG [main 

landing gear] Shock Strut was found loose, 

leading to failure of the other attachment 

bolt, subsequently resulting in failure of the 

bracket. 

This condition, if not detected and 

corrected, could prevent the MLG to extend 

to the full down-and-locked position, 

possibly resulting in MLG collapse upon 

landing or during roll-out, with consequent 

damage to the aeroplane and injury to the 

occupants. 

* * * * * 

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 12 months after the effective 

date of this AD, do a detailed inspection for 

any loose top bolt and nut of the shock strut 

actuator mounting bracket of both the lefthand and right-hand main landing gear 

(MLG), in accordance with paragraph 2.B. of 

the Accomplishment Instructions of Saab 

Service Bulletin 2000–32–073, Revision 01, 

dated October 20, 2009. 

Corrective Action 

(h) If any loose bolt or nut is found during 

the inspection required by paragraph (g) of 

this AD, before further flight, replace the bolt 

with a new bolt and accomplish paragraphs 

(h)(1) and (h)(2) of this AD, in accordance 

with paragraph 2.C. of the Accomplishment 

Instructions Saab Service Bulletin 2000–32– 

073, Revision 01, dated October 20, 2009. 

(1) Do a detailed inspection of the bottom 

bolts for uniform or fretting corrosion. If any 

corrosion is found, before further flight, 

accomplish all applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Saab Service Bulletin 2000– 

32–073, Revision 01, dated October 20, 2009. 

(2) Do a detailed inspection for damage, 

cracks, and other signs of deterioration of the 

actuator mounting bracket and shock strut. If 

signs of damage, cracks, or other signs of 

deterioration are found on the actuator 

mounting bracket or the shock strut, before 

further flight, repair in accordance with a 

method approved by the FAA or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(i) Within 12 months after the effective 

date of this AD, unless already accomplished 

in accordance with paragraph (h) of this AD, 

install the correct number of washers for both 

the top and bottom bolts of the shock strut 

actuator mounting bracket of both MLG, in 

accordance with paragraph 2.C.of the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–32–073, Revision 01, dated 

October 20, 2009. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

Saab Service Bulletin 2000–32–073, dated 

June 26, 2009, are considered acceptable for 

compliance with the corresponding actions 

specified in 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 

(k) 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; 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 

(l) Refer to MCAI EASA Airworthiness 

Directive 2010–0069, dated April 14, 2010; 

and Saab Service Bulletin 2000–32–073, 

Revision 01, dated October 20, 2009; for 

related information. 

Issued in Renton, Washington, on March 

31, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8412 Filed 4–7–11; 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] 

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), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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. * * * 

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19722 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

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. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 23, 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 W12–40, 1200 New Jersey, 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed 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. 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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0308; Directorate Identifier 

2010–NM–233–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

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 2010–0134, 

dated June 30, 2010 (referred to after 

this as ‘‘the MCAI’’), 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 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 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. 

Relevant Service Information 

328 Support Services has issued 

Service Bulletins SB–328–55–493 (for 

Model 328–100 airplanes) and SB–328J– 

55–245 (for Model 328–300 airplanes), 

both dated April 21, 2010, both 

including a Compliance Report. 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 Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 55 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

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Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19723 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

328 Support Services GmbH (Type 

Certificate Previously Held by AvCraft 

Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH): Docket 

No. FAA–2011–0308; Directorate 

Identifier 2010–NM–233–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH (Type Certificate previously 

held by AvCraft Aerospace GmbH; Fairchild 

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/ACO, 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 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

19724 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

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. 

Issued in Renton, Washington, on March 

31, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8414 Filed 4–7–11; 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] 

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); and Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 23, 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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed 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.airworth-eas@airbus.com; 

Internet http://www.airbus.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0309; Directorate Identifier 

2010–NM–255–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

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 2010–0224, 

dated November 4, 2010 (referred to 

after this as ‘‘the MCAI’’), 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 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. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A300–27–6066 (for Model 

A300–600 series airplanes) and A310– 

27–2103 (for Model A310 series 

mstockstill on DSKH9S0YB1PROD with PROPOSALS