11016 Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 

(k) Other FAA AD Provisions 

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: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2180; fax 425–227–1149. 

Information may be emailed 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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the Design Approval 

Holder with a State of Design Authority’s 

design organization approval), as applicable. 

You are required to ensure the product is 

airworthy before it is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Brazilian 

Airworthiness Directive 2012–10–01, 

effective October 29, 2012, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2014–0059. 

(2) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04256 Filed 2–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0061; Directorate 

Identifier 2013–NM–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2007–06– 

12, that applies to certain Airbus Model 

A330–200 and A330–300 airplanes. AD 

2007–06–12 requires, for certain 

airplanes, reinforcement of the structure 

of the center fuselage by installing 

external stiffeners (butt straps) at frame 

(FR) 53.3 on the fuselage skin between 

left-hand (LH) and right-hand (RH) 

stringer (STR) 13, and related 

investigative and corrective actions. 

Since we issued AD 2007–06–12, we 

have determined that the compliance 

times must be reduced in order to 

address the unsafe condition. This 

proposed AD would reduce the 

compliance times for reinforcing the 

structure of the center fuselage at FR 

53.3. We are proposing this AD to 

prevent fatigue cracking of the fuselage, 

which could result in reduced structural 

integrity of the fuselage. 

DATES: We must receive comments on 

this proposed AD by April 14, 2014. 

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. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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 by searching for 

and locating Docket No. FAA–2014– 

0061; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

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–2014–0061; Directorate Identifier 

2013–NM–029–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 

On March 7, 2007, we issued AD 

2007–06–12, Amendment 39–14993 (72 

FR 12555, March 16, 2007) (‘‘AD 2007– 

06–12’’). AD 2007–06–12 requires 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2007–06–12, 

Amendment 39–14993 (72 FR 12555, 

March 16, 2007), we have determined 

that the compliance times must be 

reduced in order to address the unsafe 

condition. We have also added the 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 11017 

compliance time for short- and longrange airplane utilization based on the 

new fatigue and damage tolerance 

evaluation. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2013– 

0016, dated January 16, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During the fatigue tests (EF2) of the Airbus 

A330 test fuselage, initiation and 

development of cracks were evidenced at the 

circumferential joint of frame 53.3. 

This condition, if not corrected, could lead 

to a reduction in the structural integrity of 

the fuselage. 

EASA issued AD 2006–0266 [(http://

ad.easa.europa.eu/blob/easa_ad_2006_0266_

Superseded.pdf/AD_2006–0266_1), which 

corresponds to FAA AD 2007–06–12, 

Amendment 39–14993 (72 FR 12555, March 

16, 2007)], which took over the requirements 

of Direction Ge ́ne ́rale de L’aviation Civile 

[DGAC] France AD F–2003–415 for A330– 

300 pre-mod 41652S11819, and required 

reinforcement of the circumferential joint of 

frame 53.3 by application of Airbus Service 

Bulletin (SB) A330–53–3143 on A330–300 

post modification 41652S11819 and pre-mod 

49202, and all A330–200 pre-mod 49202 in 

order to improve the fatigue life. 

Since that [EASA] AD was issued, in the 

frame of a new fatigue and damage tolerance 

evaluation taking into account the aeroplane 

utilisation, the thresholds for the 

reinforcement were reassessed and the 

conclusion is that some thresholds must be 

reduced. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2006–0266, which is superseded, and 

requires reinforcement of structure of the 

centre fuselage at the upper circumferential 

joint of frame 53.3 within the new 

thresholds. 

The initial compliance times range 

between 15,700 total flight cycles or 

94,600 total flight hours, whichever 

occurs first; and 25,600 total flight 

cycles or 77,000 total flight hours, 

whichever occurs first; depending on 

airplane configuration. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0061. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–53–3127 Revision 02, 

including Appendix 01, dated December 

7, 2011, and Mandatory Service Bulletin 

A330–53–3143 Revision 05, including 

Appendix 01, dated May 29, 2012. 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. 

Repair Approvals 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements of this proposed AD 

would require that the repair approval 

specifically refer to the FAA AD. This 

change is intended to clarify the method 

of compliance and to provide operators 

with better visibility of repairs that are 

specifically developed and approved to 

correct the unsafe condition. In 

addition, we use the phrase ‘‘its 

delegated agent, or the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 9 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Installation ..................... Up to 327 work-hour × $85 per hour = $27,795 $17,850 Up to $45,645 .............. Up to $410,805. 

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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
11018 Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 

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); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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. 

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 

removing airworthiness directive (AD) 

2007–06–12, Amendment 39–14993 (72 

FR 12555, March 16, 2007), and adding 

the following new AD: 

Airbus: Docket No. FAA–2014–0061; 

Directorate Identifier 2013–NM–029–AD. 

(a) Comments Due Date 

We must receive comments by April 14, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2007–06–12, 

Amendment 39–14993 (72 FR 12555, March 

16, 2007). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, and –243 airplanes; 

and A330–301, –321, –322, –323, –341, –342, 

and –343 airplanes, certificated in any 

category, except those on which Airbus 

modification 49202 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a new fatigue 

and damage tolerance evaluation that 

concluded the compliance time for an 

existing reinforcement of the fuselage has to 

be reduced. We are issuing this AD to 

prevent fatigue cracking of the fuselage, 

which could result in reduced structural 

integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation for Model A330–300 Series 

Airplanes 

For Airbus Model A330–301, A330–321, 

A330–322, A330–323, A330–341, A330–342, 

and A330–343 airplanes, except those on 

which Airbus modification 41652S11819 has 

been incorporated in production: At the time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, whichever occurs later, install butt 

straps at FR53.3 on the fuselage skin between 

left-hand (LH) and right-hand (RH) stringer 

(STR) 13, and do all related investigative and 

corrective actions before further flight. 

Except as provided by paragraph (h) of this 

AD, do all actions in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–53–3127, 

Revision 02, including Appendix 01, dated 

December 7, 2011. 

(1) At the applicable time specified in 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD. 

(i) Airplanes with a short-range mission as 

specified in Airbus Mandatory Service 

Bulletin A330–53–3127, Revision 02, dated 

December 7, 2011: Within 15,300 flight 

cycles or 46,100 flight hours, whichever 

occurs first, after the first flight of the 

airplane. 

(ii) Airplanes with a long-range mission as 

specified in Airbus Mandatory Service 

Bulletin A330–53–3127, Revision 02, dated 

December 7, 2011: Within 13,200 flight 

cycles or 79,300 flight hours, whichever 

occurs first after the first flight of the 

airplane. 

(2) Within 24 months after the effective 

date of this AD, but not to exceed 14,700 total 

flight cycles or 51,400 total flight hours, 

whichever occurs earlier. 

(h) Corrective Actions 

For Airbus Model A330–301, –321, –322, 

–323, –341, –342, and –343 airplanes, except 

those on which Airbus Modification 

41652S11819 has been incorporated in 

production: If any crack is detected during 

the related investigative actions (rototest) 

required by paragraph (g) of this AD, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the EASA (or its 

delegated agent, or by the Design Approval 

Holder (DAH) with EASA design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(i) Installation for Model A330–200 and –300 

Series Airplanes 

For airplanes specified in paragraph (c) of 

this AD on which Airbus modification 

41652S11819 has been embodied in 

production: At the time specified in 

paragraph (i)(1) or (i)(2) of this AD, 

whichever occurs later, install butt straps at 

FR53.3 on the fuselage skin between LH and 

RH STR13; and do all related investigative 

and other specified actions before further 

flight, as applicable. Do all actions in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–53–3143, Revision 05, dated 

May 29, 2012, including Appendix 1; except, 

if any crack is detected during a related 

investigative action (rototest), before further 

flight, repair the crack using a method 

approved by the Manager, International 

Branch, ANM 116, Transport Airplane 

Directorate, FAA; or the EASA (or its 

delegated agent, or by the Design Approval 

Holder (DAH) with EASA design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(1) At the applicable times specified in the 

‘‘threshold’’ column of the table in 1.E. 

‘‘Compliance’’ of Airbus Mandatory Service 

Bulletin A330–53–3143, Revision 05, dated 

May 29, 2012. Where paragraph 1.E. 

‘‘Compliance’’ of Airbus Mandatory Service 

Bulletin A330 53–3143, Revision 05, dated 

May 29, 2012, specifies a time in the 

‘‘threshold’’ column, this AD requires 

compliance within the corresponding times 

after the first flight of the airplane. 

(2) Within 24 months after the effective 

date of this AD, but not to exceed 17,600 total 

flight cycles or 61,600 total flight hours, 

whichever occurs earlier. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (g) of this AD 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A330–53–3127, Revision 01, 

including Appendix 01, dated November 21, 

2003 (which is not incorporated by reference 

in this AD). 

(2) This paragraph provides credit for 

actions required by paragraph (i) of this AD 

if those actions were performed before the 

effective date of this AD using any service 

information specified in paragraphs (j)(2)(i) 

through (j)(2)(v) of this AD; this service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–53–3143, including Appendix 01, 

dated December 24, 2004. 

(ii) Airbus Mandatory Service Bulletin 

A330–53–3143, Revision 01, including 

Appendix 01, dated June 29, 2006. 

(iii) Airbus Mandatory Service Bulletin 

A330–53–3143, Revision 02, including 

Appendix 01, dated August 31, 2010. 

(iv) Airbus Mandatory Service Bulletin 

A330–53–3143, Revision 03, including 

Appendix 01, dated March 3, 2011. 

(v) Airbus Mandatory Service Bulletin 

A330–53–3143, Revision 04, including 

Appendix 01, dated December 6, 2011. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 11019 

Branch, ANM–116, 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed 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. AMOCs approved previously for AD 

2007–06–12, Amendment 39–14993 (72 FR 

12555, March 16, 2007), are approved as 

AMOCs for the corresponding provisions of 

paragraph (i) of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0016, dated 

January 16, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0061. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04259 Filed 2–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0060; Directorate 

Identifier 2012–NM–194–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directives (AD) 2006–21– 

08, AD 2007–14–01, AD 2008–25–02, 

AD 2010–04–09, AD 2011–01–02, and 

AD 2012–16–05, for certain Airbus 

Model A330 and 340 series airplanes. 

AD 2006–21–08, AD 2007–14–01, AD 

2008–25–02, AD 2010–04–09, AD 2011– 

01–02, and AD 2012–16–05 currently 

require revising the maintenance 

program or inspection program to 

incorporate certain maintenance 

requirements and airworthiness 

limitations for fuel tank systems. Since 

we issued AD 2006–21–08, AD 2007– 

14–01, AD 2008–25–02, AD 2010–04– 

09, AD 2011–01–02, and AD 2012–16– 

05, we have determined that more 

restrictive maintenance requirements 

and airworthiness limitations are 

necessary. This proposed AD would 

require a new maintenance or 

inspection program revision. We are 

proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 14, 2014. 

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: Deliver to Mail 

address above 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, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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 by searching for 

and locating Docket No. FAA–2014– 

0060; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

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–2014–0060; Directorate Identifier 

2012–NM–194–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 

On October 10, 2006, we issued AD 

2006–21–08, Amendment 39–14793 (71 

FR 61639, October 19, 2006), for certain 

Airbus Model A330–200, A340–200, 

and A340–300 airplanes. AD 2006–21– 

08 requires installation of heat shields 

in the belly fairing of the center 

fuselage. AD 2006–21–08 resulted from 

fuel system reviews conducted by the 


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