This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

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REGISTER issue of each week.

Rules and Regulations Federal Register

8511 

Vol. 80, No. 32 

Wednesday, February 18, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0620; Directorate 

Identifier 2013–NM–238–AD; Amendment 

39–18102; AD 2015–03–06] 

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) 2007–22– 

10 for all Airbus Model A330–200, 

A330–300, A340–200, A340–300, A340– 

500, and A340–600 series airplanes. AD 

2007–22–10 required repetitive 

inspections of the left-hand and righthand wing main landing gear (MLG) rib 

6 aft bearing lugs (forward and aft) to 

detect any cracks on the two lugs, and 

replacement if necessary. Since we 

issued AD 2007–22–10, we have 

received reports of additional cracking 

of the MLG rib 6 aft bearing forward lug. 

This new AD expands the applicability 

and reduces certain compliance times. 

We are issuing this AD to detect and 

correct cracking of the MLG rib 6 aft 

bearing lugs, which could result in 

collapse of the MLG upon landing. 

DATES: This AD becomes effective 

March 25, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 25, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-2014-0620; 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0620. 

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 2007–22–10, 

Amendment 39–15246 (72 FR 61796, 

November 1, 2007; corrected November 

16, 2007 (72 FR 64532)). AD 2007–22– 

10 applied to all Airbus Model A330– 

200, A330–300, A340–200, A340–300, 

A340–500, and A340–600 series 

airplanes. The NPRM published in the 

Federal Register on September 4, 2014 

(79 FR 52585). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0271, dated November 

14, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition. The MCAI states: 

During Main Landing Gear (MLG) 

lubrication, a crack was visually found in the 

MLG rib 6 aft bearing forward lug on one 

A330 in-service aeroplane. The crack had 

extended through the entire thickness of the 

forward lug at approximately the 4 o’clock 

position (when looking forward). It has been 

determined that similar type of crack can 

develop on other aeroplane types that are 

listed in the Applicability paragraph. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the MLG attachment. 

To address this situation, Airbus issued 

inspection Service Bulletins (SB) A330–57– 

3096, A340–57–4104 and A340–57–5009 to 

instruct repetitive inspection of the gear rib 

lugs. 

Prompted by these findings, EASA issued 

Emergency AD 2006–0364–E to require 

repetitive detailed visual inspections of the 

Left Hand (LH) and Right Hand (RH) wing 

MLG rib 6 aft bearing lugs. Later EASA 

issued AD 2007–0247R1–E, which 

superseded EAD 2006–0364–E, to: 

—Expand the applicability to all A330 and 

A340 aeroplanes, because the interference 

fit bushes cannot be considered as a 

terminating action, owing to unknown root 

cause; and 

—Add a second parameter quoted in Flight 

Hours (FH) to the inspection interval in 

order to reflect the aeroplane utilization in 

service. 

EASA AD 2007–0247R1–E was 

republished to correct a typographical error. 

Since the first crack finding and issuance 

of the inspection SBs and related ADs, six 

further cracks have been reported. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA EAD 

2007–0247 R1–E and retains its 

requirements, is issued to expand the 

applicability to the newly certified models 

A330–223F and A330–243F and to reduce 

the threshold further to the risk assessment 

of recent in-service experience. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2014-0620-0004. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter, an anonymous individual, 

supported the NPRM (79 FR 52585, 

September 4, 2014). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

52585, September 4, 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 52585, 

September 4, 2014). 

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8512 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

bulletins: 

• Airbus Service Bulletin A330–57– 

3096, Revision 5, dated October 17, 

2013. 

• Airbus Service Bulletin A340–57– 

4104, Revision 4, dated October 17, 

2013. 

• Airbus Service Bulletin A340–57– 

5009, Revision 3, dated October 17, 

2013. 

The service information describes 

procedures for detailed inspections of 

the MLG rib 6 forward and aft lugs for 

cracking. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

Costs of Compliance 

We estimate that this AD affects 81 

airplanes of U.S. registry. 

We estimate that it will take about 2 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work hour. 

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 $13,770, or $170 per 

product. 

We have no definitive data that would 

enable us to provide a cost estimate for 

the on-condition actions specified in 

this AD. 

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-2014-0620; 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) 

2007–22–10, Amendment 39–15246 (72 

FR 61796, November 1, 2007; corrected 

November 16, 2007 (72 FR 64532)), and 

adding the following new AD: 

2015–03–06 Airbus: Amendment 39–18102, 

Docket No. FAA–2014–0620; Directorate 

Identifier 2013–NM–238–AD. 

(a) Effective Date 

This AD becomes effective March 25, 2015. 

(b) Affected ADs 

This AD replaces AD 2007–22–10, 

Amendment 39–15246 (72 FR 61796, 

November 1, 2007; corrected November 16, 

2007 (72 FR 64532)). 

(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, –313, –541, and 

–642 airplanes; certificated in any category; 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking of the main landing gear (MLG) rib 

6 aft bearing forward lug. We are issuing this 

AD to detect and correct cracking of the MLG 

rib 6 aft bearing lugs, which could result in 

collapse of the MLG upon landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within 42 months since the airplane’s first 

flight or since the last MLG support rib 

replacement, as applicable; or within 4 

months after the effective date of this AD; 

whichever occurs later: Do a detailed 

inspection for cracking of the left-hand and 

right-hand wing MLG rib 6 aft bearing lugs 

(forward and aft), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3096, Revision 05, 

dated October 17, 2013; (for Model A330– 

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

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

–342, and –343 airplanes); A340–57–4104, 

Revision 04, dated October 17, 2013 (for 

Model A340–211, –212, –213, –311, –312, 

–313 airplanes); or A340–57–5009, Revision 

03, dated October 17, 2013 (for Model A340– 

541 and –642 airplanes); as applicable. 

Repeat the inspections at the times specified 

in paragraphs (g)(1) through (g)(7) of this AD, 

as applicable. 

(1) For Model A330–201, –202, –203, –223, 

and –243 airplanes, repeat the inspections at 

intervals not to exceed 300 flight cycles or 

1,500 flight hours, whichever occurs first. 

(2) For Model A330–223F and –243F 

airplanes, repeat the inspections at intervals 

not to exceed 300 flight cycles or 900 flight 

hours, whichever occurs first. 

(3) For Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

repeat the inspections at intervals not to 

exceed 300 flight cycles or 900 flight hours, 

whichever occurs first. 

(4) For Model A340–211, –212, and –213 

airplanes, repeat the inspections at intervals 

not to exceed 200 flight cycles or 800 flight 

hours, whichever occurs first. 

(5) For Model A340–311 and –312 

airplanes; and Model A340–313 airplanes 

(except weight variant (WV) 27), repeat the 

inspections at intervals not to exceed 200 

flight cycles or 800 flight hours, whichever 

occurs first. 

(6) For Model A340–313 (only WV27) 

airplanes, repeat the inspections at intervals 

not to exceed 200 flight cycles or 400 flight 

hours, whichever occurs first. 

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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8513 

(7) For Model A340–541 and –642 

airplanes, repeat the inspections at intervals 

not to exceed 100 flight cycles or 500 flight 

hours, whichever occurs first. 

(h) Corrective Action 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, replace the cracked 

MLG support rib 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. Replacement of 

an MLG support rib does not terminate the 

repetitive inspections required by paragraph 

(g) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions required by paragraph 

(g) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service bulletin 

identified in paragraphs (i)(1) through (i)(12) 

of this AD. 

(1) Airbus Service Bulletin A330–57A3096, 

dated December 5, 2006, which was 

incorporated by reference in AD 2007–03–04, 

Amendment 39–14915 (72 FR 4416, January 

31, 2007), on February 15, 2007. 

(2) Airbus Service Bulletin A330–57A3096, 

Revision 01, dated April 18, 2007, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A330–57–3096, 

excluding appendix 01, Revision 02, dated 

August 13, 2007, which was incorporated by 

reference in AD 2007–22–10, Amendment 

39–15246 (72 FR 61796, November 1, 2007; 

corrected November 16, 2007 (72 FR 64532)), 

on November 16, 2007. 

(4) Airbus Service Bulletin A330–57–3096, 

Revision 03, dated October 24, 2012, which 

is not incorporated by reference in this AD. 

(5) Airbus Service Bulletin A330–57–3096, 

Revision 04, dated February 6, 2013, which 

is not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A340–57A4104, 

dated December 5, 2006, which was 

incorporated by reference in AD 2007–03–04, 

Amendment 39–14915 (72 FR 4416, January 

31, 2007), on February 15, 2007. 

(7) Airbus Service Bulletin A340–57–4104, 

Revision 01, dated August 13, 2007, which is 

not incorporated by reference in this AD. 

(8) Airbus Service Bulletin A340–57–4104, 

excluding appendix 01, Revision 02, dated 

September 5, 2007, which was incorporated 

by reference in AD 2007–22–10, Amendment 

39–15246 (72 FR 61796, November 1, 2007; 

corrected November 16, 2007 (72 FR 64532)), 

on November 16, 2007. 

(9) Airbus Service Bulletin A340–57–4104, 

Revision 03, dated October 24, 2012, which 

is not incorporated by reference in this AD. 

(10) Airbus Service Bulletin A340– 

57A5009, dated December 5, 2006, which 

was incorporated by reference in AD 2007– 

03–04, Amendment 39–14915 (72 FR 4416, 

January 31, 2007), on February 15, 2007. 

(11) Airbus Service Bulletin A340–57– 

5009, excluding appendix 01, Revision 01, 

dated August 13, 2007, which was 

incorporated by reference in AD 2007–22–10, 

Amendment 39–15246 (72 FR 61796, 

November 1, 2007; corrected November 16, 

2007 (72 FR 64532)), on November 16, 2007. 

(12) Airbus Service Bulletin A340–57– 

5009, Revision 02, dated October 24, 2012, 

which is not incorporated by reference in this 

AD. 

(j) 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0271, dated 

November 14, 2013, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!documentDetail;D=

FAA-2014-0620-0004. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(l) 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 A330–57–3096, 

Revision 05, dated October 17, 2013. 

(ii) Airbus Service Bulletin A340–57–4104, 

Revision 04, dated October 17, 2013. 

(iii) Airbus Service Bulletin A340–57– 

5009, Revision 03, dated October 17, 2013. 

(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 February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02672 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0484; Directorate 

Identifier 2013–NM–245–AD; Amendment 

39–18101; AD 2015–03–05] 

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) 2012–09– 

07 for certain Airbus Model A319–111, 

–112, and –132 airplanes; Model A320– 

111, –211, –212, –214, and –232 

airplanes; and Model A321–111, –211, 

–212, and –231 airplanes. AD 2012–09– 

07 required an electrical bonding test 

between the gravity fill re-fuel adaptor 

and the top skin panels on the wings; 

and, if necessary, an inspection for 

corrosion of the component interface 

and adjacent area; and repairing the 

gravity fuel adaptor if necessary. This 

new AD adds airplanes to the 

applicability and requires inspecting 

those airplanes to determine if a repair 

was done, and doing the electrical 

bonding test and corrective action if 

necessary. This AD was prompted by a 

determination that more airplanes are 

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