45550 Federal Register / Vol. 83, No. 175 / Monday, September 10, 2018 / Rules and Regulations 

Boeing Alert Requirements Bulletin 737– 

53A1370 RB, dated December 13, 2017. 

(h) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD: 

Where Boeing Alert Requirements Bulletin 

737–53A1370 RB, dated December 13, 2017, 

uses the phrase ‘‘the original issue date of 

Requirements Bulletin 737–53A1370 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(2) Where Boeing Alert Requirements 

Bulletin 737–53A1370 RB, dated December 

13, 2017, specifies contacting Boeing, this AD 

requires repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(3) Where Step 2. of Appendix A of Boeing 

Alert Requirements Bulletin 737–53A1370 

RB, dated December 13, 2017, specifies 

‘‘Electrically close the door,’’ this AD allows 

closing the door electrically or manually. 

(4) Where Step 6. of Appendix A of Boeing 

Alert Requirements Bulletin 737–53A1370 

RB, dated December 13, 2017, specifies to 

‘‘Cycle the door electrically and make sure it 

operates smoothly,’’ this AD allows cycling 

the door electrically or manually and making 

sure it operates smoothly. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO 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 manager of the 

certification office, send it to the attention of 

the person identified in paragraph (j) of this 

AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, FAA, to make those findings. 

To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(4) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (i)(4)(i) and (i)(4)(ii) 

of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

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. 

(j) Related Information 

For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Section, Los Angeles ACO Branch, 

FAA, 3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5324; fax: 

562–627–5210; email: galib.abumeri@faa.gov. 

(k) 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) Boeing Alert Requirements Bulletin 

737–53A1370 RB, dated December 13, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.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 

August 21, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18740 Filed 9–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0789; Product 

Identifier 2018–NM–120–AD; Amendment 

39–19395; AD 2018–18–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2018–12– 

08, which applied to certain Airbus SAS 

Model A330–200 and –300 series 

airplanes, and Model A340–212, –213, 

–312, and –313 airplanes. AD 2018–12– 

08 required repetitive inspections of 

certain fastener holes, and related 

investigative and corrective actions if 

necessary. This new AD corrects certain 

compliance time references. This AD 

was prompted by a report of cracking at 

fastener holes located at a certain frame 

(FR) on the lower shell panel junction. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective September 

25, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 22, 2018 (83 FR 33821, July 

18, 2018). 

We must receive comments on this 

AD by October 25, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EAL, Rond-Point 

Emile Dewoitine No: 2, 31700 Blagnac 


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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– 

0789. 

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– 

0789; 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 

Docket Operations (telephone 800–647– 

5527) is listed above. Comments will be 

available in the AD docket shortly after 

receipt. 

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 AD 2018–12–08, 

Amendment 39–19312 (83 FR 33821, 

July 18, 2018) (‘‘AD 2018–12–08’’), 

which applied to certain Airbus SAS 

Model A330–200 and -300 series 

airplanes, and Model A340–212, –213, 

–312, and –313 airplanes. AD 2018–12– 

08 was prompted by a report of cracking 

at fastener holes located at FR40 on the 

lower shell panel junction. AD 2018– 

12–08 required repetitive inspections of 

certain fastener holes, and related 

investigative and corrective actions if 

necessary. We issued AD 2018–12–08 to 

address cracking at FR40 on the lower 

shell panel junction; such cracking 

could lead to reduced structural 

integrity of the fuselage. 

Since we issued AD 2018–12–08, we 

have determined that it is necessary to 

correct certain service bulletin table 

references, which provide the 

compliance times for the initial 

inspection. Table 1 to paragraph (g)(1) of 

AD 2018–12–08 pointed to ‘‘table 1’’ of 

the service information for the initial 

compliance time. However, table 2 and 

table 3 in the service bulletins also 

apply to certain airplanes (those in 

Configuration 1). All airplanes 

belonging to affected U.S. operators are 

in Configuration 2 or Configuration 3, 

which use only table 1 in the service 

bulletins. This AD corrects the service 

bulletin table references for the 

compliance times. We have changed 

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

removing the limitation to ‘‘table 1’’ of 

the service bulletins, and instead 

referring to the compliance times in 

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

service bulletins. 

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 SAS 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 

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, 

Amendment 39–18845 (82 FR 18547, April 

20, 2017) (‘‘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 included Model 

A340–211 airplanes in its applicability. 

Airbus SAS 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 SAS 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 on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2018–0789. 

Related Service Information Under 1 

CFR Part 51 

Airbus SAS has issued Service 

Bulletin A330–53–3215, Revision 03, 

dated January 22, 2018; and 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. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 


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MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Justification and Determination 

of the Effective Date 

This AD corrects an error that affects 

compliance for non-U.S.-registered 

airplanes only. Therefore, we find good 

cause that notice and opportunity for 

prior public comment are unnecessary. 

In addition, for the reason stated above, 

we find that good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2018–0789; 

Product Identifier 2018–NM–120–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 99 

airplanes of U.S. registry. This AD adds 

no new economic burden. The current 

costs for this AD are repeated for the 

convenience of affected operators, as 

follows: 

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 

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 and associated appliances 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) 

2018–12–08, Amendment 39–19312 (83 

FR 33821, July 18, 2018), and adding the 

following new AD: 

2018–18–16 Airbus SAS: Amendment 39– 

19395; Docket No. FAA–2018–0789; 

Product Identifier 2018–NM–120–AD. 


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(a) Effective Date 

This AD is effective September 25, 2018. 

(b) Affected ADs 

This AD replaces AD 2018–12–08, 

Amendment 39–19312 (83 FR 33821, July 18, 

2018) (‘‘AD 2018–12–08’’). 

(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 SAS Modification 44360 has been 

embodied in production. 

(1) Airbus SAS Model A330–201, –202, 

–203, –223, –243, –301, –302, –303, –321, 

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

(2) Airbus SAS 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 address this cracking, 

which could lead to reduced structural 

integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Compliance Times for 

Paragraph (h) of This AD, With Corrected 

Compliance Time Locations 

This paragraph restates the requirements of 

paragraph (g) of AD 2018–12–08, with 

corrected compliance time locations in table 

1 to paragraph (g)(1) 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 

(‘‘SB A330–53–3215R3’’); or Airbus Service 

Bulletin A340–53–4215, Revision 02, dated 

November 23, 2016 (‘‘SB A340–53–4215R2’’); 

as applicable, depending on airplane 

utilization and configuration. As of August 

22, 2108 (the effective date of AD 2018–12– 

08), where paragraph 1.E., ‘‘Compliance,’’ of 

SB A330–53–3215R3, 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. 

(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 SB A330–53–3215R3 or SB 

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

A340–53–4215R2, as applicable, depending 

on airplane utilization and configuration. 

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

A330–53–3215R3 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) Retained Repetitive Inspections and 

Related Investigative and Corrective 

Actions, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2018–12–08, with no 

changes. At the applicable compliance time 

specified in paragraph (g) of this AD: 

Accomplish a special detailed inspection of 

the 10 fastener holes located at FR40 on the 

lower shell panel junction on both left-hand 

and right-hand sides, in accordance with the 

Accomplishment Instructions of SB A330– 

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

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

where SB A330–53–3215R3 or SB A340–53– 

4215R2 specifies to contact Airbus SAS for 

repair instructions, and specifies that action 

as ‘‘RC’’ (required for compliance), 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 SAS’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 SB A330–53–3215R3 or SB 

A340–53–4215R2, as applicable, and SB 

A330–53–3215R3 or SB A340–53–4215R2 

specifies to contact Airbus SAS 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 SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized 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 indicated 

otherwise as specified in the method 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus SAS’s EASA DOA. 


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(i) Retained Reporting Provision, With No 

Changes 

This paragraph restates the provisions of 

paragraph (i) of AD 2018–12–08, with no 

changes. Although SB A330–53–3215R3 and 

SB A340–53–4215R2 specify to submit 

certain information to the manufacturer, and 

specify that action as RC, this AD does not 

include that requirement. 

(j) Retained Credit for Previous Actions, 

With Revised Formatting 

This paragraph restates the provisions of 

paragraph (j) of AD 2018–12–08, with a 

reformatted service bulletin listing. This 

paragraph provides credit for the inspections 

required by the introductory text of 

paragraph (h) of this AD and the related 

investigative and corrective actions specified 

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 

the applicable service information specified 

in paragraphs (j)(1) through (j)(5) of this AD. 

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

dated June 21, 2013. 

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

Revision 01, dated April 17, 2014. 

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

Revision 02, dated November 23, 2016. 

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

dated June 21, 2013. 

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

Revision 01, dated April 17, 2014. 

(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 

SAS’s EASA DOA. If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as specified 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 

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–2018–0789. 

(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)(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. 

(3) The following service information was 

approved for IBR on August 22, 2018. 

(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. 

(4) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, Rond-Point Emile Dewoitine 

No: 2, 31700 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. 

(5) 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. 

(6) 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 

August 29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19437 Filed 9–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2017–1051; Airspace 

Docket No. 17–AGL–21] 

RIN 2120–AA66 

Revocation of Class E Airspace; 

Springfield, OH 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action removes Class E 

airspace areas designated as an 

extension to a Class D surface area at 

Springfield-Beckley Municipal Airport, 

Springfield, OH. This action is required 

as a result of an airspace review, which 

inadvertently overlooked the removal of 

the associated Class E airspace 

extensions when the Class D airspace 

was removed. 

DATES: Effective 0901 UTC, November 8, 

2018. The Director of the Federal 

Register approves this incorporation by 

reference action under Title 1 Code of 

Federal Regulations part 51, subject to 

the annual revision of FAA Order 

7400.11 and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.11B, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at http://www.faa.gov/ 

air_traffic/publications/. For further 

information, you can contact the 

Airspace Policy Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW, Washington, DC 20591; 

telephone: (202) 267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of FAA 

Order 7400.11B at NARA, call (202) 

741–6030, or go to https://

www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

FAA Order 7400.11, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. 

FOR FURTHER INFORMATION CONTACT: 

Rebecca Shelby, Federal Aviation 

Administration, Operations Support 

Group, Central Service Center, 10101 

Hillwood Parkway, Fort Worth, TX 

76177; telephone (817) 222–5857. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 


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