Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33821 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Section, FAA, Seattle 

ACO Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206–231– 

3528; email: allen.rauschendorfer@faa.gov. 

(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 the AD specifies otherwise. 

(i) Aviation Partners Boeing Service 

Bulletin AP767–57–013, Revision 1, dated 

April 11, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Aviation Partners Boeing, 

2811 S 102nd Street, Suite 200, Seattle, WA 

98168; telephone 206–762–1171; internet 

https://www.aviationpartnersboeing.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on June 

12, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13362 Filed 7–17–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0111; Product 

Identifier 2017–NM–059–AD; Amendment 

39–19312; AD 2018–12–08] 

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) 2017–07– 

07, which applied to certain Airbus 

Model A330–200, A330–300, A340–200, 

and A340–300 series airplanes. AD 

2017–07–07 required repetitive 

inspections of certain fastener holes, 

and related investigative and corrective 

actions if necessary. This AD retains the 

requirements of AD 2017–07–07 and 

expands the applicability. This AD was 

prompted by a report of cracking at 

fastener holes located at frame (FR) 40 

on the lower shell panel junction. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 22, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 22, 2018. 

ADDRESSES: For service information 

identified in this final rule, 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 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0111. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0111; 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 address for the 

Docket Office (telephone: 800–647– 

5527) is 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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax: 206–231–3229. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–07–07, 

Amendment 39–18845 (82 FR 18547, 

April 20, 2017) (‘‘AD 2017–07–07’’). AD 

2017–07–07 applied to certain Airbus 

Model A330–200, A330–300, A340–200, 

and A340–300 series airplanes with 

manufacturer serial numbers (MSN) 

0176 through 0915 inclusive. The 

NPRM published in the Federal 

Register on February 20, 2018 (83 FR 

7117). The NPRM was prompted by a 

report of cracking at fastener holes 

located at frame FR40 on the lower shell 

panel junction. The NPRM proposed to 

retain the requirements of AD 2017–07– 

07 and expand the applicability. We are 

issuing this AD to detect and correct 

cracking at FR40 on the lower shell 

panel junction; such cracking could lead 

to reduced structural integrity of the 

fuselage. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0063, 

dated April 12, 2017 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200, 

A330–300, and A340–200 series 

airplanes, and Model A340–312 and 

–313 airplanes. The MCAI states: 

During full scale fatigue test of the Frame 

(FR) 40 to fuselage skin panel junction, 

fatigue damage was found. Corrective actions 

consisted of in-service installation of an 

internal reinforcing strap on the related 

junction, as currently required by DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France AD 1999–448–126(B), which refers to 

Airbus Service Bulletin (SB) A340–53–4104 

Revision 02, and [DGAC] AD 2001–070(B), 

which refers to Airbus SB A330–53–3093 

Revision 04; retrofit improvement of internal 

reinforcing strap fatigue life through 

recommended Airbus SB A330–53–3145; and 


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33822 Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 

introducing a design improvement in 

production through Airbus mod 44360. 

After those actions were implemented, 

cracks were found on both left-hand (LH) and 

right-hand (RH) sides on internal strap, butt 

strap, keel beam fitting, or forward fitting 

FR40 flange. These findings were made 

during embodiment of a FR40 web repair on 

an A330 aeroplane, and during keel beam 

replacement on an A340 aeroplane, where 

the internal strap was removed and a special 

detailed inspection (SDI) was performed on 

several holes. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the centre fuselage of the aeroplane. 

Prompted by these findings, Airbus issued 

SB A330–53–3215 and SB A340–53–4215, 

providing inspection instructions. 

Consequently, EASA issued AD 2014–0136 

[which corresponds to FAA AD 2017–07–07] 

to require repetitive SDI (rototest) of 10 

fastener holes located at the FR40 lower shell 

panel junction on both LH and RH sides and, 

depending on findings, accomplishment of 

applicable corrective action(s). 

Since that [EASA] AD was issued, 

prompted by the results of complementary 

fatigue analyses, it was determined that postmod 55792 aeroplanes could be also affected 

by crack initiation and propagation at this 

area of the fuselage. These analyses 

demonstrated that post-mod 55792 

aeroplanes must follow the same 

maintenance program as aeroplanes in postmod 55306 and pre-mod 55792 

configuration. Consequently, Airbus 

published SB A330–53–3215 Revision 02 and 

SB A340–53–4215 Revision 02 to expand the 

Effectivity accordingly. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0136, which is superseded, which 

now also apply to aeroplanes in post-mod 

55792 configuration [the applicability 

identifies airplanes in post-mod 44360 

configuration]. 

AD 2017–07–07 includes Model 

A340–211 airplanes in its applicability. 

Airbus Model A340–211 airplanes are 

not identified in the applicability of this 

AD because those airplanes are not 

affected by the identified unsafe 

condition. All of those airplanes are in 

the pre-Airbus modification 44360 

configuration. The MCAI also does not 

include Model A340–211 airplanes in 

its applicability. 

The compliance time ranges between 

20,000 flight cycles or 65,400 flight 

hours and 20,800 flight cycles or 68,300 

flight hours, depending on airplane 

utilization and configuration. The 

repetitive inspection interval ranges 

between 14,000 flight cycles or 95,200 

flight hours and 24,600 flight cycles or 

98,700 flight hours, depending on 

airplane utilization and configuration. 

You may examine the MCAI in the AD 

docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0111. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Kenneth Ciallella supported the NPRM. 

Explanation of Changes Made to This 

AD 

We have revised this AD to refer to 

Airbus Service Bulletin A330–53–3215, 

Revision 03, dated January 22, 2018, as 

the appropriate source of service 

information for the required actions. 

This service information incorporates 

minor editorial changes which have no 

effect on airplanes that have 

incorporated prior revisions of this 

service information. We have revised 

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

and paragraphs (g), (g)(1), (g)(2), (h), 

(h)(1), (h)(2), and (i) of this AD to 

specify Airbus Service Bulletin A330– 

53–3215, Revision 03, dated January 22, 

2018, as the appropriate source of 

service information for accomplishing 

the required actions in those 

paragraphs. 

We have revised paragraph (j) of this 

AD to give credit for using Airbus 

Service Bulletin A330–53–3215, 

Revision 02, dated November 23, 2016, 

to accomplish the required actions 

before the effective date of this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Airbus Service 

Bulletin A330–53–3215, Revision 03, 

dated January 22, 2018 (‘‘A330–53– 

3215, R3’’) and Airbus Service Bulletin 

A340–53–4215, Revision 02, dated 

November 23, 2016. This service 

information describes procedures for 

repetitive rototest inspections of certain 

fastener holes, and related investigative 

and corrective actions if necessary. 

These documents are distinct since they 

apply to different airplane models. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 99 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

42 work-hours × $85 per hour = $3,570 ..................................................................................... $0 $3,570 $353,430 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

required inspections. We have no way 

of determining the number of aircraft 

that might need these repairs: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

46 work-hours × $85 per hour = $3,910 ................................................................................................................. $2,358 $6,268 


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Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33823 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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. 

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) 

2017–07–07, Amendment 39–18845 (82 

FR 18547, April 20, 2017), and adding 

the following new AD: 

2018–12–08 Airbus: Amendment 39–19312; 

Docket No. FAA–2018–0111; Product 

Identifier 2017–NM–059–AD. 

(a) Effective Date 

This AD is effective August 22, 2018. 

(b) Affected ADs 

This AD replaces AD 2017–07–07, 

Amendment 39–18845 (82 FR 18547, April 

20, 2017) (‘‘AD 2017–07–07’’). 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD, all 

manufacturer serial numbers on which 

Airbus Modification 44360 has been 

embodied in production. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

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

(2) Airbus Model A340–212, –213, –312, 

and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

cracking at fastener holes located at frame 

(FR) 40 on the lower shell panel junction. We 

are issuing this AD to detect and correct 

cracking at FR40 on the lower shell panel 

junction; such cracking could lead to reduced 

structural integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Compliance Times for the Actions 

Required by Paragraph (h) of This AD 

Accomplish the actions required by 

paragraph (h) of this AD at the times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, as applicable. 

(1) For airplanes having serial numbers 

0176 through 0915 inclusive: Within the 

compliance times defined in table 1 to 

paragraph (g)(1) of this AD, and, thereafter, 

at intervals not to exceed the compliance 

times defined in Airbus Service Bulletin 

A330–53–3215, Revision 03, dated January 

22, 2018 (‘‘A330–53–3215, R3’’); or Airbus 

Service Bulletin A340–53–4215, Revision 02, 

dated November 23, 2016 (‘‘A340–53–4215, 

R2’’); as applicable, depending on airplane 

utilization and configuration. As of the 

effective date of this AD, where paragraph 

1.E. ‘‘Compliance,’’ of A330–53–3215, R3 

specifies weight variant (WV) 050 in the 

condition column of table 1, configuration 

003, for the purposes of this AD, WV060 and 

WV080 are also included. 


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33824 Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 

(2) For all airplanes except those identified 

in paragraph (g)(1) of this AD: Before 

exceeding the applicable compliance time 

‘‘threshold’’ defined in paragraph 1.E., 

‘‘Compliance,’’ of A330–53–3215, R3; or 

A340–53–4215, R2; as applicable, depending 

on airplane utilization and configuration and 

to be counted from airplane first flight, and, 

thereafter, at intervals not to exceed the 

compliance times specified in paragraph 1.E., 

‘‘Compliance’’ of A330–53–3215, R3; or 

A340–53–4215, R2; as applicable, depending 

on airplane utilization and configuration. 

Where paragraph 1.E. ‘‘Compliance,’’ of 

A330–53–3215, R3 specifies weight variant 

WV050 in the condition column of table 1, 

configuration 003, for the purposes of this 

AD, WV060 and WV080 are also included. 

(h) Repetitive Inspections and Related 

Investigative and Corrective Actions 

At the applicable compliance times 

specified in paragraph (g) of this AD: 

Accomplish a special detailed inspection of 

the 10 fastener holes located at FR40 lower 

shell panel junction on both left-hand and 

right-hand sides, in accordance with the 

Accomplishment Instructions of A330–53– 

3215, R3; or A340–53–4215, R2; as 

applicable. 

(1) If, during any inspection required by 

the introductory text of paragraph (h) of this 

AD, any crack is detected, before further 

flight, accomplish all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of A330–53–3215, R3; or A340– 

53–4215, R2; as applicable, except where 

A330–53–3215, R3; or A340–53–4215, R2; 

specifies to contact Airbus for repair 

instructions, and specifies that action as 

‘‘RC,’’ this AD requires repair before further 

flight using a method approved by the 

Manager, International Section, Transport 

Standards Branch, FAA; or 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. 

(2) If, during any inspection required by 

the introductory text of paragraph (h) of this 

AD, the diameter of a fastener hole is found 

to be outside the tolerances of the transition 

fit as specified in A330–53–3215, R3; or 

A340–53–4215, R2; as applicable; and A330– 

53–3215, R3; or A340–53–4215, R2; specifies 

to contact Airbus for repair instructions, and 

specifies that action as ‘‘RC,’’ before further 

flight, repair using a method approved by the 

Manager, International Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Accomplishment of corrective actions, 

as required by paragraph (h)(1) of this AD, 

does not constitute terminating action for the 

repetitive inspections required by the 

introductory text of paragraph (h) of this AD. 

(4) Accomplishment of a repair on an 

airplane, as required by paragraph (h)(2) of 

this AD, does not constitute terminating 

action for the repetitive inspections required 

by the introductory text of paragraph (h) of 

this AD for that airplane, unless the method 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus’s EASA DOA indicates 

otherwise. 

(i) No Reporting Requirement 

Although A330–53–3215, R3 and A340– 

53–4215, R2, specify to submit certain 

information to the manufacturer, and specify 

that action as ‘‘RC,’’ this AD does not include 

that requirement. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

inspections required by the introductory text 

of (h) of this AD and the related investigative 

and corrective actions required by paragraph 

(h)(1) of this AD, if those actions were 

performed before May 25, 2017 (the effective 

date of AD 2017–07–07), using Airbus 

Service Bulletin A330–53–3215, dated June 

21, 2013; or Revision 01, dated April 17, 

2014; or Revision 02, dated November 23, 

2016; or Airbus Service Bulletin A340–53– 

4215, dated June 21, 2013; or Revision 01, 

dated April 17, 2014; as applicable. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 Section, send it 

to the attention of the person identified in 

paragraph (l)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(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 Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (g)(1), (g)(2), (h)(1), 

(h)(2), and (i) of this AD: If any service 

information contains procedures or tests that 

are identified as RC, those procedures and 

tests must be done to comply with this AD; 

any procedures or tests that are not identified 

as RC are recommended. Those procedures 

and tests that are not identified as RC may 

be deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 


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Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33825 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0063, dated April 12, 2017, for related 

information. This MCAI may be found in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–0111. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax: 206–231–3229. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–53–3215, 

Revision 03, dated January 22, 2018. 

(ii) Airbus Service Bulletin A340–53–4215, 

Revision 02, dated November 23, 2016. 

(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 Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13220 Filed 7–17–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Bureau of Indian Affairs 

[189A2100DD/AAKC001030/ 

A0A501010.999900 253G] 

25 CFR Part 83 

RIN 1076–AF41 

Change of Address; Office of Federal 

Acknowledgment 

AGENCY: Bureau of Indian Affairs, 

Interior. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: The Bureau of Indian Affairs 

(BIA) is amending its regulations to 

reflect a change of address for the Office 

of Federal Acknowledgment. This rule 

is a technical amendment that corrects 

the address for filing petitions for 

Federal acknowledgment as an Indian 

Tribe. 

DATES: Effective July 18, 2018. 

FOR FURTHER INFORMATION CONTACT: 

Elizabeth Appel, Director, Office of 

Regulatory Affairs & Collaborative 

Action, (202) 273–4680; 

elizabeth.appel@bia.gov. 

SUPPLEMENTARY INFORMATION: This rule 

updates the address for the Office of 

Federal Acknowledgment to reflect the 

office’s change in location. 

Procedural Requirements 

A. Regulatory Planning and Review 

(E.O. 12866 and 13563) 

Executive Order (E.O.) 12866 provides 

that the Office of Information and 

Regulatory Affairs (OIRA) at the Office 

of Management and Budget (OMB) will 

review all significant rules. OIRA has 

determined that this rule is not 

significant. 

E.O. 13563 reaffirms the principles of 

E.O. 12866 while calling for 

improvements in the nation’s regulatory 

system to promote predictability, to 

reduce uncertainty, and to use the best, 

most innovative, and least burdensome 

tools for achieving regulatory ends. The 

E.O. directs agencies to consider 

regulatory approaches that reduce 

burdens and maintain flexibility and 

freedom of choice for the public where 

these approaches are relevant, feasible, 

and consistent with regulatory 

objectives. E.O. 13563 emphasizes 

further that regulations must be based 

on the best available science and that 

the rulemaking process must allow for 

public participation and an open 

exchange of ideas. The Department has 

developed this rule in a manner 

consistent with these requirements. 

B. Regulatory Flexibility Act 

This rule will not have a significant 

economic effect on a substantial number 

of small entities under the Regulatory 

Flexibility Act (RFA) (5 U.S.C. 601 et 

seq.). The rule is administrative in 

nature and affects only a mailing 

address. 

C. Small Business Regulatory 

Enforcement Fairness Act 

This rule is not a major rule under 5 

U.S.C. 804(2), the Small Business 

Regulatory Enforcement Fairness Act. It 

will not result in the expenditure by 

State, local, or tribal governments, in the 

aggregate, or by the private sector of 

$100 million or more in any one year. 

The rule’s requirements will not result 

in a major increase in costs or prices for 

consumers, individual industries, 

Federal, State, or local government 

agencies, or geographic regions. Nor will 

this rule have significant adverse effects 

on competition, employment, 

investment, productivity, innovation, or 

the ability of the U.S.-based enterprises 

to compete with foreign-based 

enterprises. 

D. Unfunded Mandates Reform Act 

This rule does not impose an 

unfunded mandate on State, local, or 

Tribal governments or the private sector 

of more than $100 million per year. The 

rule does not have a significant or 

unique effect on State, local, or Tribal 

governments or the private sector. A 

statement containing the information 

required by the Unfunded Mandates 

Reform Act (2 U.S.C. 1531 et seq.) is not 

required. 

E. Takings (E.O. 12630) 

Under the criteria in Executive Order 

12630, this rule does not affect 

individual property rights protected by 

the Fifth Amendment nor does it 

involve a compensable ‘‘taking.’’ A 

takings implication assessment is 

therefore not required. 

F. Federalism (E.O. 13132) 

Under the criteria in Executive Order 

13132, this rule has no 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. This rule 

corrects a mailing address. 

G. Civil Justice Reform (E.O. 12988) 

This rule complies with the 

requirements of Executive Order 12988. 

Specifically, this rule meets the criteria 

of section 3(a) requiring all regulations 

be reviewed to eliminate errors and 

ambiguity and be written to minimize 


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