70458 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

(2) For all airplanes: As of the effective 

date of this AD, no person may install an 

NLG having P/N 201071001 or 201071002 on 

any airplane. 

(r) Credit for Previous Actions 

This paragraph provides credit for the 

replacement required by paragraph (l) of this 

AD, if those actions were performed before 

the effective date of this AD using Fokker 

Service Bulletin SBF 100–32–119, dated 

January 31, 2000, provided P/N 201071003 or 

201071004 nose gear has been installed. 

(s) 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: 

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. 

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) Contacting the Manufacturer: As of the 

effective date of this AD, 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 Fokker Services B.V.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(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. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0002R1, dated 

March 30, 2012, for related information. You 

may examine the MCAI in the AD docket on 

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

#!documentDetail;D=FAA-2014-0062-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (u)(5) and (u)(6) of this AD. 

(u) 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. 

(3) The following service information was 

approved for IBR on December 31, 2014. 

(i) Fokker Service Bulletin SBF 100–32– 

119, Revision 1, dated November 15, 2011, 

including Fokker Manual Change 

Notification MCNM–F100–043, dated 

January 31, 2000. 

(ii) Fokker Proforma Service Bulletin SBF 

100–32–149, Revision 1, dated October 25, 

2007, including Appendix 1, dated December 

12, 2006. 

(iii) Fokker Service Bulletin SBF 100–53– 

074, dated November 1, 1999. 

(4) The following service information was 

approved for IBR on October 3, 2000 (65 FR 

52298, August 17, 2000). 

(i) Fokker Service Bulletin SBF100–32– 

118, dated October 8, 1999. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. 

(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 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27361 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0425; Directorate 

Identifier 2013–NM–180–AD; Amendment 

39–18024; AD 2014–23–08] 

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) 2012–06– 

19 for certain Airbus Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes; and Model A340–200 

and –300 series airplanes. AD 2012–06– 

19 required repetitive inspections of the 

main fitting and sliding tube of the nose 

landing gear (NLG) for defects, damage, 

and cracks; and corrective actions if 

necessary. This new AD requires an 

inspection of the part number and serial 

number of the NLG main fitting and 

NLG sliding tube; for affected parts, this 

new AD requires a magnetic particle 

inspection (MPI) for cracks, and flap 

peening and replacement if necessary. 

This new AD also requires, for certain 

parts, additional inspections for damage 

and cracking. This new AD also adds 

airplanes to the applicability. This AD 

was prompted by reports of a cracked 

main fitting and sliding tube during 

NLG overhaul. We are issuing this AD 

to detect and correct cracks, defects, or 

damage of the main fitting or sliding 

tube, which could result in consequent 

NLG collapse. 

DATES: This AD becomes effective 

December 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 30, 2012 (77 FR 

22188, April 13, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0425; 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. 

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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 2012–06–19, 

Amendment 39–17000 (77 FR 22188, 

April 13, 2012). AD 2012–06–19 applied 

to certain Airbus Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes; and Model A340–200 

and –300 series airplanes. The NPRM 

published in the Federal Register on 

June 30, 2014 (79 FR 36666). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0179, 

dated August 7, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model 

A340–200 and –300 series airplanes. 

The MCAI states: 

During the overhaul of two different Nose 

Landing Gear (NLG) units, cracks were found 

on the main fitting of one and the sliding 

tube of the other. Investigations concluded 

that the cracks initiated as a result of residual 

stress in the parts, following damage due to 

impact during towing incidents. 

A subsequent review of the reported 

incidents identified a specific group of NLG 

main fittings and sliding tubes that may have 

sustained impact damage as a result of 

towing incidents. 

This condition, if not detected and 

corrected could lead to NLG collapse. 

To address this potential unsafe condition, 

EASA issued AD 2010–0034 [(http://

ad.easa.europa.eu/blob/easa_ad_2010_0034_

Corrected_superseded.pdf/AD_2010-0034_1) 

[which corresponds to FAA AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012)] to require accomplishment of a 

one-time Magnetic Particles Inspection (MPI), 

followed by repetitive Detailed Visual 

Inspections (DVI) of the main fittings and 

sliding tubes of the affected NLG units 

identified by Part Number (P/N) and Serial 

Number (S/N) in the Applicability section of 

that AD and, depending on findings, 

accomplishment of applicable corrective 

actions. 

Since that [EASA] AD was issued, it has 

been found necessary to address the issue at 

the level of NLG detail parts and no longer 

at NLG assembly level, as some detail parts 

have been transferred from an aeroplane to 

another. Airbus revised the applicable 

Service Bulletins (SB), which now list the 

affected NLG main fittings and sliding tubes. 

For the reasons described above, this 

[EASA] AD retains [certain] requirements of 

EASA AD 2010–0034 which is superseded 

and requires [an inspection of the part 

number and serial number of the NLG main 

fitting and NLG sliding tube, and for affected 

parts,] a one-time MPI [for cracks], followed 

by repetitive DVI [for cracking, damage to 

paint, sealant, cadmium, and base metal] of 

the affected NLG main fittings and sliding 

tubes and, depending on inspection results, 

accomplishment of corrective actions [e.g., 

flap peening and replacing cracked parts]. 

This AD also extends the applicability to 

A330 freighters. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0425- 

0002. 

Clarification of Service Information 

References 

We have clarified the service 

information references in this AD to 

identify the appendices. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 36666, 

June 30, 2014) and the FAA’s response 

to each comment. 

Request to Reference Service 

Information Instead of Table 

Air France requested that we revise 

paragraph (g) of the NPRM (79 FR 

36666, June 30, 2014), to replace table 

1 to paragraph (g) of the NPRM with 

references to Airbus Service Bulletin 

A330–32–3233, Revision 02, including 

Appendix 01, dated January 27, 2014; 

and Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 

01, dated July 5, 2013. Air France 

asserted that the main reason for 

superseding AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, 

April 13, 2012), is to address the issue 

at the level of NLG detail parts and no 

longer at the NLG assembly level, as 

some detail parts have been transferred 

from one airplane to another. 

We agree with the commenter that 

Airbus Service Bulletin A330–32–3233, 

Revision 02, including Appendix 01, 

dated January 27, 2014; and Airbus 

Service Bulletin A340–32–4275, 

Revision 01, including Appendix 01, 

dated July 5, 2013, contain the NLG 

detail parts (NLG main fitting and NLG 

sliding tube). However, paragraph (g) of 

this AD is a requirement that is retained 

from AD 2012–06–19, Amendment 39– 

17000 (77 FR 22188, April 13, 2012) and 

only restates the affected parts 

identified in that AD. Paragraphs (i) and 

(j) of this AD require inspecting for 

affected NLG main fittings and NLG 

sliding tubes identified in the service 

information and inspecting affected 

parts for cracks. Accomplishing the new 

requirements specified in paragraph (j) 

of this AD terminates the actions 

specified in paragraph (g) of this AD. 

Therefore, no changes were made to this 

AD in this regard. 

‘‘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. 

We have become 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 ADmandated 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 

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70460 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

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. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (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. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 

36666, June 30, 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 36666, 

June 30, 2014). 

Costs of Compliance 

We estimate that this AD affects 92 

airplanes of U.S. registry. 

The actions that were required by AD 

2012–06–19, Amendment 39–17000 (77 

FR 22188, April 13, 2012), that are 

retained in this AD take about 4 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2012–06–19 is $31,280 per product. 

We also estimate that it will take 

about 10 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $78,200, or $850 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 114 work-hours and require parts 

costing $435,000, for a cost of $444,690 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0425; 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) 

2012–06–19, Amendment 39–17000 (77 

FR 22188, April 13, 2012), and adding 

the following new AD: 

2014–23–08 Airbus: Amendment 39–18024. 

Docket No. FAA–2014–0425; Directorate 

Identifier 2013–NM–180–AD. 

(a) Effective Date 

This AD becomes effective December 31, 

2014. 

(b) Affected ADs 

This AD replaces AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

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(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of a 

cracked nose landing gear (NLG) main fitting 

and sliding tube during NLG overhaul. We 

are issuing this AD to detect and correct 

cracks, defects, or damage of the main fitting 

or sliding tube, which could result in 

consequent NLG collapse. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Detailed Inspection and 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012), with revised service information. 

For Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes; and Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes; if fitted with the NLG identified in 

table 1 to paragraph (g) of this AD: Within 

900 flight hours after April 30, 2012 (the 

effective date of AD 2012–06–19), do a 

detailed inspection of the NLG main fitting 

and sliding tube for any cracks, defects, and 

damage of the paint or surface protection, 

including paint removal and cracking of the 

surface treatment. Before further flight after 

doing the detailed inspection of the NLG, 

remove the labels, paint, surface protection 

coatings, and cadmium from the NLG main 

fitting; do a detailed inspection for any 

damage to the surface that will impair the 

magnetic particle inspection (MPI); and, if 

any defects are found, before further flight, 

remove any defects by polishing. Do all 

actions specified in this paragraph in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (g)(1) or 

(g)(2) of this AD. 

(1) For Model A330 airplanes: Airbus 

Mandatory Service Bulletin A330–32–3233, 

dated October 22, 2009; or Airbus Service 

Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014. 

(2) For Model A340 airplanes: Airbus 

Mandatory Service Bulletin A340–32–4275, 

dated October 22, 2009; or Airbus Service 

Bulletin A340–32–4275, Revision 01, 

including Appendix 01, dated July 5, 2013. 

TABLE 1 TO PARAGRAPH (g) OF THIS

AD—APPLICABLE NLG AND SERIAL

NUMBERS

Part No. Serial No. 

D23285200 ............................... B2 

D23285101–7 ........................... B58 

D23285101–10 ......................... B75 

D23581100–1 ........................... B124 

D23581100–1 ........................... B159 

D23581100–7 ........................... B386 

D23581100–7 ........................... B398 

D23581100–7 ........................... B400 

TABLE 1 TO PARAGRAPH (g) OF THIS

AD—APPLICABLE NLG AND SERIAL

NUMBERS—Continued 

Part No. Serial No. 

D23581100–7 ........................... B403 

(h) Retained Magnetic Particle Inspection 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012), with revised service information. 

Before further flight after doing the actions 

required in paragraph (g) of this AD: Do an 

MPI for cracking of the NLG main fitting and 

sliding tube, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) If no crack is detected during the MPI 

required by the introductory text of 

paragraph (h) of this AD: Before further 

flight, flap peen the inspected area where the 

paint and cadmium has been removed, and 

replace the protective coatings, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(2) If any crack is detected during the MPI 

required by the introductory text of 

paragraph (h) of this AD: Before further 

flight, replace the damaged part with a new 

or serviceable part, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(i) New Identification of Part and Serial 

Numbers 

Within 1,000 flight hours after the effective 

date of this AD, identify the part number and 

serial number of the NLG main fitting and 

NLG sliding tube, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 01, 

dated July 5, 2013; as applicable. A review 

of airplane maintenance records is acceptable 

in lieu of this identification if the part 

number and the serial number of the NLG 

main fitting and NLG sliding tube can be 

conclusively determined from that review. 

(j) New Magnetic Particle Inspection 

If, during the identification required by 

paragraph (i) of this AD, it is determined any 

NLG main fitting or NLG sliding tube is 

installed and the fitting or tube has a part 

number and serial number listed in Airbus 

Service Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 01, 

dated July 5, 2013; as applicable: Within 

1,000 flight hours after the effective date of 

this AD, do an MPI for cracks of the affected 

parts, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 01, 

dated July 5, 2013; as applicable. 

Accomplishing the MPI required by this 

paragraph terminates the inspections 

required by paragraphs (g) and (h) of this AD. 

(1) If any crack is detected during the MPI 

required by the introductory text of 

paragraph (j) of this AD: Before further flight, 

replace any cracked part (NLG main fitting 

and NLG sliding tube) with a serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 01, 

dated July 5, 2013; as applicable. 

(2) If no crack is detected during the MPI 

required by the introductory text of 

paragraph (j) of this AD: Before further flight, 

do a flap peening to introduce compressive 

residual stress and corrosion protection, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, including Appendix 

01, dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, 

including Appendix 01, dated July 5, 2013; 

as applicable. 

(k) New Detailed Inspection 

Within 900 flight hours after doing the flap 

peening required by paragraph (j)(2) of this 

AD, do a detailed inspection for damage to 

paint, damage to the sealant around the 

labels, damage to the cadmium or base metal, 

and for cracking of the affected parts, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, including Appendix 

01, dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, 

including Appendix 01, dated July 5, 2013; 

as applicable. Repeat the inspection 

thereafter at intervals not to exceed 900 flight 

hours. 

(1) If any damage to the paint, damage to 

the sealant around the labels, or damage to 

the cadmium or base metal, is detected 

during any detailed inspection required by 

the introductory text of paragraph (k) of this 

AD; Before further flight, do an MPI for 

cracking of the affected parts, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3233, 

Revision 02, including Appendix 01, dated 

January 27, 2014; or Airbus Service Bulletin 

A340–32–4275, Revision 01, including 

Appendix 01, dated July 5, 2013; as 

applicable. 

(2) If any cracking is detected during any 

inspection required by the introductory text 

of paragraph (k) or paragraph (k)(1) of this 

AD: Before further flight, replace any cracked 

part with a serviceable part, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3233, 

Revision 02, including Appendix 01, dated 

January 27, 2014; or Airbus Service Bulletin 

A340–32–4275, Revision 01, including 

Appendix 01, dated July 5, 2013; as 

applicable. 

(l) Terminating Action 

Replacement of a part as required by 

paragraph (j)(1) or (k)(2) of this AD is 

terminating action for the repetitive detailed 

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70462 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

inspections required by paragraph (k) of this 

AD for that part, provided that the part 

number and serial number of the replacement 

part is not listed in Airbus Service Bulletin 

A330–32–3233, Revision 02, including 

Appendix 01, dated January 27, 2014; or 

Airbus Service Bulletin A340–32–4275, 

Revision 01, including Appendix 01, dated 

July 5, 2013; as applicable. 

(m) Parts Installation Limitation 

As of the effective date of this AD, 

installation of an NLG main fitting or NLG 

sliding tube having a part number and serial 

number listed in Airbus Service Bulletin 

A330–32–3233, Revision 02, including 

Appendix 01, dated January 27, 2014; or 

Airbus Service Bulletin A340–32–4275, 

Revision 01, including Appendix 01, dated 

July 5, 2013; as applicable; is allowed, 

provided that the NLG main fitting and NLG 

sliding tube have not accumulated more than 

900 flight hours since the most recent 

inspection accomplished in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

including Appendix 01, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, including Appendix 01, 

dated July 5, 2013; as applicable. 

(n) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraphs (j) and (k) 

of this AD and the flap peening required by 

paragraph (j)(2) of this AD, if those actions 

were performed before the effective date of 

this AD using the applicable service 

information specified in paragraph (n)(1), 

(n)(2), or (n)(3) of this AD. 

(1) Airbus Service Bulletin A330–32–3233, 

dated October 22, 2009. 

(2) Airbus Service Bulletin A330–32–3233, 

Revision 01, dated July 5, 2013. This 

document is not incorporated by reference in 

this AD. 

(3) Airbus Service Bulletin A340–32–4275, 

dated October 22, 2009. 

(o) 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: 

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. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0179, dated August 7, 2013, 

for related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0425-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) 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. 

(3) The following service information was 

approved for IBR on December 31, 2014. 

(i) Airbus Service Bulletin A330–32–3233, 

Revision 02, including Appendix 01, dated 

January 27, 2014. 

(ii) Airbus Service Bulletin A340–32–4275, 

Revision 01, including Appendix 01, dated 

July 5, 2013. 

(4) The following service information was 

approved for IBR on April 30, 2012, (77 FR 

22188, April 13, 2012). 

(i) Airbus Service Bulletin A330–32–3233, 

dated October 22, 2009. 

(ii) Airbus Service Bulletin A340–32–4275, 

dated October 22, 2009. 

(5) 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. 

(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 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27360 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

U.S. Customs and Border Protection 

19 CFR Part 4 

[CBP Dec. 14–11] 

Technical Amendment: Boarding of 

Vessels at CBP Ports 

AGENCY: U.S. Customs and Border 

Protection, Department of Homeland 

Security. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This document amends the 

U.S. Customs and Border Protection 

(CBP) regulations to conform to U.S. 

Coast Guard implementing regulations 

regarding certain boardings of vessels 

under the Maritime Transportation Act 

of 2002, as amended (MTSA). Under 

MTSA, any person boarding a vessel 

arriving at a CBP port after that vessel 

is taken in charge by a CBP officer must 

comply with Transportation Worker 

Identification Credential requirements. 

This document also updates 

terminology and removes obsolete 

language in the relevant regulatory 

section. 

DATES: Effective November 26, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Craig Clark, Office of Field Operations, 

U.S. Customs and Border Protection, 

(202) 344–3052, OFO-ManifestBranch@

cbp.dhs.gov. 

SUPPLEMENTARY INFORMATION: 

I. Background 

It is the policy of U.S. Customs and 

Border Protection (CBP) to periodically 

review title 19 of the Code of Federal 

Regulations (19 CFR) to ensure that it is 

accurate and up-to-date so that the 

general public is aware of CBP 

requirements and procedures. As part of 

this review policy, CBP has determined 

that certain corrections affecting part 4 

of the CBP regulations (19 CFR part 4) 

are necessary. 

A. Maritime Transportation Act of 2002 

The Maritime Transportation Act of 

2002 (MTSA), Pub. L. 107–295, 116 Stat. 

2064, as amended by the Security and 

Accountability for Every Port Act of 

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