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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8514 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 

subject to the identified unsafe 

condition. We are issuing this AD to 

detect and correct corrosion and 

improper bonding, which, in 

combination with a lightning strike in 

this area, could create a source of 

ignition in a fuel tank, resulting in a fire 

or explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

March 25, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication 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-2014-0484; 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, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@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–2014–0484. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–09–07, 

Amendment 39–17042 (77 FR 28238, 

May 14, 2012). AD 2012–09–07 applied 

to 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. The NPRM 

published in the Federal Register on 

July 30, 2014 (79 FR 44144). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0277R1, dated December 

4, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The MCAI states: 

Cases of corrosion findings were reported 

on the overwing refueling aperture (used to 

fill the fuel tank by gravity) on the wing top 

skin. The reported corrosion was on the 

mating surface of the aperture flange, 

underneath the refuel adaptor. Corrosion 

findings have been repaired on a case by case 

basis in accordance with approved data. 

For certain aeroplanes, the repair provided 

by Airbus contained instructions to apply 

primer coating on the mating surface. Since 

doing those repairs, it has been found that 

this primer coating may prevent proper 

electrical bonding provision between the 

overwing refueling cap adaptor and the wing 

skin. 

This condition, if not detected and 

corrected, could, in combination with a 

lightning strike in this area, create a source 

of ignition in a fuel tank, possibly resulting 

in a fire or explosion and consequent loss of 

the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2011–0034 [http://

ad.easa.europa.eu/blob/easa_ad_2011_

0034.pdf/AD_2011-0034] to require a onetime electrical bonding check between the 

gravity fill re-fuel adaptor and the top skin 

panels on the affected aeroplanes (identified 

by MSN [manufacturer serial number] in the 

applicability section of that [EASA] AD) and, 

in case of findings, the accomplishment of 

applicable corrective actions. 

Since that [EASA] AD was issued, EASA 

has been made aware that some operators 

may inadvertently have applied an Airbus 

repair, approved for only one aeroplane 

MSN, to other aeroplanes, without requesting 

a revision of the repair to add aeroplanes, or 

to notify Airbus of such action(s). 

Consequently, the condition addressed by 

EASA AD 2011–0034 could affect more 

aeroplanes than initially determined. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0034, which is superseded, and 

expands the Applicability to all A320 family 

aeroplane Models, all MSN. 

This [EASA] AD has been revised to amend 

and clarify paragraph (3), and to correct an 

error in the Type/Model designations on page 

1, where the A318 was inadvertently omitted. 

For the newly added airplanes, required 

actions include inspecting for the 

presence of a corrosion repair on an 

overwing refueling aperture, and doing 

the electrical bonding test and 

applicable corrective actions if a repair 

has been installed. You may examine 

the MCAI in the AD docket on the 

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

!documentDetail;D=FAA-2014-0484- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 44144, 

July 30, 2014) and the FAA’s response 

to the comment. 

Request To Include Revised Service 

Information 

United Airlines (UAL) asked that we 

include a statement in the NPRM (79 FR 

44144, July 30, 2014), which allows 

performing the required actions in 

accordance with the instructions of 

Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013. 

UAL stated that the revised service 

information specifies the same method 

of inspection as specified in Airbus 

Service Bulletin A320–57–1152, dated 

June 14, 2010. UAL further stated that 

Revision 01 of this service bulletin also 

provides operators with updated repair 

instructions that were not available in 

the original issue of this service 

bulletin. 

We agree with the commenter’s 

request. Since issuance of the NPRM (79 

FR 44144, July 30, 2014), Airbus has 

issued Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013. 

This revision states that no additional 

work is necessary on airplanes changed 

in accordance with Airbus Service 

Bulletin A320–57–1152, dated June 14, 

2010, which was specified as the 

appropriate source of service 

information in the NPRM (79 FR 44144, 

July 30, 2014). 

We have changed paragraph (g) of this 

AD to specify Airbus Service Bulletin 

A320–57–1152, Revision 01, dated 

December 19, 2013. We have also added 

a new paragraph (h) to this AD to give 

credit for actions done before the 

effective date of this AD using Airbus 

Service Bulletin A320–57–1152, dated 

June 14, 2010, and redesignated 

subsequent paragraphs accordingly. 

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 

44144, July 30, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8515 

proposed in the NPRM (79 FR 44144, 

July 30, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1152, Revision 01, dated 

December 19, 2013. The service 

information describes procedures for 

inspecting certain airplanes to 

determine if a repair was done, and 

doing an electrical bonding test and 

corrective action if necessary. This 

service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

The actions required by AD 2012–09– 

07, Amendment 39–17042 (77 FR 

28238, May 14, 2012), and retained in 

this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2012–09–07 is 

$170 per product. 

We also estimate that it takes 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 cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $144,670, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 11 work-hours, for a cost of $935 

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-2014-0484; 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) 

2012–09–07, Amendment 39–17042 (77 

FR 28238, May 14, 2012), and adding 

the following new AD: 

2015–03–05 Airbus: Amendment 39–18101. 

Docket No. FAA–2014–0484; Directorate 

Identifier 2013–NM–245–AD. 

(a) Effective Date 

This AD becomes effective March 25, 2015. 

(b) Affected ADs 

This AD replaces AD 2012–09–07, 

Amendment 39–17042 (77 FR 28238, May 14, 

2012). 

(c) Applicability 

(1) This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers, except airplanes identified in 

paragraph (c)(2) of this AD. 

(2) Airplanes that have been delivered from 

production with Airbus Modification 38209 

(Removal of the Outer Wing Refueling 

Aperture) incorporated, and without Airbus 

Modification 38206 (Re-introduction of the 

Outer Wing Refueling Aperture) 

incorporated, are not affected by the 

requirements of this AD. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that more airplanes are subject to the 

identified unsafe condition. We are issuing 

this AD to detect and correct corrosion and 

improper bonding, which, in combination 

with a lightning strike in this area, could 

create a source of ignition in a fuel tank, 

resulting in a fire or explosion and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Electrical Bonding Test, and 

General Visual Inspection if Necessary, With 

Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–09–07, 

Amendment 39–17042 (77 FR 28238, May 14, 

2012), with revised repair approval language 

and revised service information. For 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; certificated in any 

category; having manufacturer serial numbers 

0039, 0078, 0109, 0118, 0120, 0153, 0174, 

0187, 0203, 0215, 0218, 0226, 0227, 0228, 

0236, 0237, 0269, 0270, 0278, 0285, 0286, 

0287, 0288, 0294, 0301, 0337, 0377, 0462, 

0463, 0464, 0465, 0520, 0523, 0528, 0876, 

0888, 0921, 0935, 0974, 1014, 1102, 1130, 

1160, 1162, 1177, 1215, 1250, 1287, 1336, 

1388, 1404, 1444, 1449, 1476, 1505, 1524, 

1564, 1605, 1616, 1622, 1640, 1645, 1658, 

1677, 1691, 1729, and 1905: Within 24 

months after June 18, 2012 (the effective date 

of AD 2012–09–07), do an electrical bonding 

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8516 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 

test to check for bonding between the re-fuel 

adaptor of the gravity fill and the top skin 

panels on the left-hand and right-hand wings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, Revision 01, dated December 19, 

2013. 

(1) If the resistance value is 10 milliohms 

or less at the left-hand and right-hand wing, 

no further action is required by this 

paragraph. 

(2) If the resistance value is greater than 10 

milliohms at the left-hand or right-hand 

wing, before further flight, do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013. If any 

corrosion is found during the inspection, 

before further flight, repair the gravity fill 

fuel adaptor, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1152, Revision 01, 

dated December 19, 2013; except where 

Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013, 

specifies to contact Airbus, 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 DOAauthorized signature. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–57–1152, dated June 14, 2010, 

which was incorporated by reference in AD 

2012–09–07, Amendment 39–17042 (77 FR 

28238, May 14, 2012). 

(i) New Requirement of This AD: 

Maintenance Check/Electrical Bonding Test 

and Corrective Action if Necessary 

For airplanes other than those identified in 

paragraph (g) of this AD: Within 24 months 

after the effective date of this AD, determine 

whether a corrosion repair has been done on 

an overwing refueling aperture, whereby a 

primer coating has been applied on the 

mating surface of the aperture flange. A 

review of the airplane maintenance records is 

acceptable to make this determination, 

provided that whether a primer coat was 

applied can be conclusively determined from 

that review. 

(1) If it is determined that a primer coating 

was applied on the mating surface of the 

aperture flange; or if a determination cannot 

be made, or the outcome is inconclusive: 

Within 24 months after the effective date of 

this AD do the electrical bonding test 

specified in paragraph (g) of this AD, and 

before further flight, do all applicable actions 

specified in paragraph (g)(2) of this AD. 

(2) If it is determined that a corrosion 

repair has not been done, and a primer 

coating has not been applied on the mating 

surface of the aperture flange since first entry 

into service, no further action is required by 

this paragraph. 

(j) Corrosion Repair Provision 

As of the effective date of this AD, any 

corrosion repair done on an overwing 

refueling aperture on any airplane must 

comply with the repair requirements of 

paragraph (g)(2) of 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 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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 

2012–09–07, Amendment 39–17042 (77 FR 

28238, May 14, 2012), are approved as 

AMOCs for the corresponding provisions of 

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 

EASA; or Airbus’s EASA 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 2013–0277R1, dated 

December 4, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2014-0484-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (m)(4) and (m)(5) 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 A320–57–1152, 

Revision 01, dated December 19, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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 

4, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02697 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–2014–0522; Directorate 

Identifier 2014–NM–087–AD; Amendment 

39–18100; AD 2015–03–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This AD was 

prompted by reports of fuselage skin 

cracks at the lower forward corner of the 

main entry door (MED) 1 cutout. This 

AD requires repetitive inspections of the 

fuselage skin of the MED 1 cutout for 

cracking, and repair if necessary; and 

also provides an optional terminating 

modification, including post-repair or 

post-modification fuselage skin 

inspections for cracking, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct skin cracking, 

which can become large and could 

adversely affect the structural integrity 

of the airplane. 

DATES: This AD is effective March 25, 

2015. 

mstockstill on DSK4VPTVN1PROD with RULES