52184 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

(6) 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. 

(7) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20258 Filed 9–2–14; 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; Amendment 

39–17949; AD 2014–16–25] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–06– 

12 for certain Airbus Model A330–200 

and A330–300 airplanes. This new AD 

reduces the compliance times for 

reinforcing the structure of the center 

fuselage. This AD was prompted by a 

new fatigue and damage tolerance 

evaluation that revealed 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. 

DATES: This AD becomes effective 

October 8, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 8, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0061; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC. 

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 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. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–06–12, 

Amendment 39–14993 (72 FR 12555, 

March 16, 2007). AD 2007–06–12 

applied to certain Airbus Model A330– 

200 and A330–300 airplanes. The 

NPRM published in the Federal 

Register on February 27, 2014 (79 FR 

11016). 

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 certain Airbus Model A330–200 and 

A330–300 airplanes. 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. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0061- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 11016, February 27, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 11016, February 

27, 2014), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was 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 proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 11016, February 27, 2014) 

about these proposed changes. However, 

a comment was provided for an NPRM 


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having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013) pointed out that in many cases the 

foreign manufacturer’s service bulletin 

and the foreign authority’s MCAI might 

have been issued some time before the 

FAA AD. Therefore, the DOA might 

have provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘DAH with State of 

Design Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

11016, February 27, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 11016, 

February 27, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 9 

airplanes of U.S. registry. 

We estimate that it will take about 327 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$17,850 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be up to $410,805, 

or up to $45,645 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 that 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); 

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. 


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52186 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=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 

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. 

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 

removing Airworthiness Directive (AD) 

2007–06–12, Amendment 39–14993 (72 

FR 12555, March 16, 2007), and adding 

the following new AD: 

2014–16–25 Airbus: Amendment 39–17949. 

Docket No. FAA–2014–0061; Directorate 

Identifier 2013–NM–029–AD. 

(a) Effective Date 

This AD becomes effective October 8, 2014. 

(b) Affected ADs 

This AD replaces 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 Model 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 

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) For airplanes with a short-range mission 

as specified in Airbus Service Bulletin A330– 

53–3127, Revision 02, including Appendix 

01, 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) For airplanes with a long-range mission 

as specified in Airbus Service Bulletin A330– 

53–3127, Revision 02, including Appendix 

01, 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 European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(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 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 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(1) At the applicable times specified in the 

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

‘‘Compliance’’ of Airbus Service Bulletin 

A330–53–3143, Revision 05, including 

Appendix 01, dated May 29, 2012. Where 

paragraph 1.E. ‘‘Compliance’’ of Airbus 

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 paragraph (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 was incorporated by reference in 

AD 2005–20–07, Amendment 39–14300 (70 

FR 57732, October 4, 2005). 

(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. 

(i) Airbus Service Bulletin A330–53–3143, 

including Appendix 01, dated December 24, 

2004, which is not incorporated by reference 

in this AD. 

(ii) Airbus Service Bulletin A330–53–3143, 

Revision 01, including Appendix 01, dated 

June 29, 2006, which was incorporated by 

reference in AD 2007–06–12, Amendment 

39–14993 (72 FR 12555, March 16, 2007). 

(iii) Airbus Service Bulletin A330–53– 

3143, Revision 02, including Appendix 01, 

dated August 31, 2010, which is not 

incorporated by reference in this AD. 

(iv) Airbus Service Bulletin A330–53– 

3143, Revision 03, including Appendix 01, 

dated March 3, 2011, which is not 

incorporated by reference in this AD. 

(v) Airbus Service Bulletin A330–53–3143, 

Revision 04, including Appendix 01, dated 

December 6, 2011, which is not incorporated 

by reference in this AD. 

(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 


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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 52187 

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. 

(i) 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. 

(ii) 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0016, dated 

January 16, 2013, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0061-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–53–3127, 

Revision 02, dated December 7, 2011, 

including Appendix 01. 

(ii) Airbus Service Bulletin A330–53–3143, 

Revision 05, dated May 29, 2012, including 

Appendix 01. 

(3) 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. 

(4) 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. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

7, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19725 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0794; Directorate 

Identifier 2012–NM–157–AD; Amendment 

39–17936; AD 2014–16–12] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Dassault Aviation Model FALCON 

2000EX airplanes. This AD was 

prompted by a revision to the airplane 

airworthiness limitations to introduce a 

corrosion prevention control program, 

among other changes, to the 

maintenance requirements and 

airworthiness limitations. This AD 

requires revising the maintenance or 

inspection program to include the 

maintenance tasks and airworthiness 

limitations specified in the 

airworthiness limitations section of the 

airplane maintenance manual. We are 

issuing this AD to prevent reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

October 8, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 8, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0794; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Dassault Falcon Jet, 

P.O. Box 2000, South Hackensack, NJ 

07606; telephone 201–440–6700; 

Internet http://www.dassaultfalcon.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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

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 by adding an AD that would 

apply to all Dassault Aviation Model 

FALCON 2000EX airplanes. The NPRM 

published in the Federal Register on 

September 25, 2013 (78 FR 58973). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0157, 

dated August 23, 2012 (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: 

The airworthiness limitations and 

maintenance requirements for the Falcon 

2000EX type design are included in Dassault 

Aviation Falcon 2000EX (F2000EX) Aircraft 

Maintenance Manual (AMM) chapter 5–40 

and are approved by the European Aviation 

Safety Agency (EASA). EASA issued AD 

2008–0221 [http://ad.easa.europa.eu/ad/

2008-0221.pdf] to require accomplishment of 

the maintenance tasks, and implementation 

of the airworthiness limitations, as specified 

in Dassault Aviation F2000EX AMM chapter 

5–40 at revision 3. 

Since that [EASA] AD was issued, Dassault 

Aviation issued F2000EX AMM chapter 5–40 

at revision 7, which introduces new or more 

restrictive maintenance requirements and/or 

airworthiness limitations. 

Dassault Aviation AMM chapter 5–40 

revision 7 contains among other changes the 

following requirements: 

—Inspection and test of horizontal stabilizer 

jackscrew; 

—Test of various components of the 

electrical power system; 

—Revised Time Between Overhaul for 

screwjack of flap actuators -3 version; 

—Revised interval for checking the screw/nut 

play on screwjack of flap actuators -3 

version; 


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