22354 Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 

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 (m) 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, 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) AMOCs approved previously for AD 

2014–12–13 are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (h) of this AD. 

(5) Except as required by paragraph (j)(1) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (l)(5)(i) and (l)(5)(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 sub-step is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

sub-step. 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. 

(m) Related Information 

For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(n) 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 Service Bulletin 737– 

57A1318, Revision 1, dated July 22, 2016. 

(ii) Boeing Alert Service Bulletin 737– 

57A1328, dated July 22, 2016. 

(3) For Boeing 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; 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 

April 27, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–09864 Filed 5–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1245; Product 

Identifier 2017–NM–099–AD; Amendment 

39–19266; AD 2018–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes Republication 

Republication 

Editorial Note: Rule document 2018–09280 

was originally published on pages 19925 

through 19928 in the issue of Monday, May 

7, 2018. In that publication, on page 19927, 

in Table 1 to paragraph (g) of this AD, the last 

line was omitted from the table. The 

corrected document is published here in its 

entirety. 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318 series airplanes and 

Model A319 series airplanes; all Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and all Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. This AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the holes of the upper 

cleat to upper stringer attachments at 

certain areas of the left- and right-hand 

wings are subject to widespread fatigue 

damage (WFD). This AD requires 

modifying the holes of the upper cleat 

to upper stringer attachments at certain 

areas of the left- and right-hand wings. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective June 11, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 11, 2018. 

ADDRESSES: For service information 

identified in this final rule, 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. 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–2017– 

1245. 

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–2017– 

1245; 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 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St, Des Moines, WA 98198; 

telephone and fax 206–231–3223. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A318 

series airplanes and Model A319 series 

airplanes; all Model A320–211, –212, 

–214, –216, –231, –232, and –233 

airplanes; and all Model A321–111, 

–112, –131, –211, –212, –213, –231, and 


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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22355 

–232 airplanes. The NPRM published in 

the Federal Register on January 12, 

2018 (83 FR 1579) (‘‘the NPRM’’). The 

NPRM was prompted by an evaluation 

by the DAH indicating that the holes of 

the upper cleat to upper stringer 

attachments at certain areas of the leftand right-hand wings are subject to 

WFD. The NPRM proposed to require 

modifying the holes of the upper cleat 

to upper stringer attachments at certain 

areas of the left- and right-hand wings. 

We are issuing this AD to prevent 

fatigue cracking in the stringer 

attachment holes of the wings, which 

could result in reduced structural 

integrity of the wings. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0117, 

dated July 7, 2017 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A318 series 

airplanes and Model A319 series 

airplanes; all Model A320–211, –212, 

–214, –216, –231, –232, and –233 

airplanes; and all Model A321–111, 

–112, –131, –211, –212, –213, –231, and 

–232 airplanes. The MCAI states: 

Within the scope of work of service life 

extension for A320 aeroplanes and of 

widespread fatigue damage evaluations, it 

has been determined that a structural 

modification is required to allow the 

aeroplanes to continue operation up to the 

limit of validity (LoV). 

This condition, if not corrected, may affect 

the structural integrity of the wing. 

To address this potential unsafe condition, 

Airbus issued [service bulletin] SB A320–57– 

1208, providing instructions to oversize the 

holes of the upper cleat to upper stringer 

attachments at Rib 2 to Rib 7 (inclusive). 

For the reason described above, this 

[EASA] AD requires modification of the 

affected holes. 

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–2017– 

1245. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. United 

Airlines agreed with the intent of the 

NPRM. 

Request To Clarify Applicability 

Allegiant Air asked that we clarify the 

manufacturer serial numbers (MSNs) 

identified in the applicability section of 

the proposed AD. Allegiant Air stated 

that the effectivity specified in Airbus 

Service Bulletin A320–57–1208, dated 

November 21, 2016, identifies airplanes 

up to and including MSN 7493, and 

asked about airplanes having MSNs 

higher than 7493. Allegiant Air noted 

that it has 11 Model A320 airplanes 

with MSNs outside those listed in 

Airbus Service Bulletin A320–57–1208, 

dated November 21, 2016. Allegiant Air 

added that it understands the AD takes 

precedence over the service 

information, but there are several 

configurations listed therein. Allegiant 

Air also added that since the MSNs in 

question are not listed in the effectivity 

of the service information, an operator 

with an MSN outside the effectivity will 

not know which modification kit to 

order. 

We agree to clarify. The effectivity in 

Airbus Service Bulletin A320–57–1208, 

dated November 21, 2016, does not 

include all MSNs for Model A320 

airplanes, and the applicability 

specified in paragraph (c) of this AD 

includes all MSNs for Model A320 

airplanes, except for airplanes having 

certain modifications. We acknowledge 

that the referenced service information 

may not be adequate for certain airplane 

configurations. Therefore, we have 

revised paragraph (g) of this AD to 

provide an option for doing the 

modification, including identification of 

the appropriate modification kit, using a 

method approved by the Manager, 

International Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA Design Organization 

Approval (DOA). 

In addition, Airbus has informed us 

that Revision 1 of the referenced service 

information will expand the effectivity 

to include MSNs up to 8555. Airbus has 

also informed us that, upon request, it 

will issue a technical adaptation as an 

interim method of compliance until a 

revised service bulletin is issued. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM 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 A320–57–1208, dated 

November 21, 2016. This service 

information describes procedures for 

modifying the stringer attachments at 

rib 2 through rib 7 of the left- and righthand wings. The modification includes 

oversizing the holes, doing an eddy 

current inspection of the affected holes 

for damage, and repair. 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 1,136 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification (by oversizing and doing eddy 

current inspection).

125 work-hours × $85 per hour = $10,625 .... $26,260 $36,885 $41,901,360 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 


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‘‘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 adding 

the following new airworthiness 

directive (AD): 

2018–09–09 Airbus: Amendment 39–19266; 

Docket No. FAA–2017–1245; Product 

Identifier 2017–NM–099–AD. 

(a) Effective Date 

This AD is effective June 11, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

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 A320–211, 

–212, –214, –216, –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 specified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model A318 series airplanes on which 

Airbus Modification (Mod) 39195 has been 

embodied in production or Airbus Service 

Bulletin A320–00–1219 has been embodied 

in service. 

(2) Model A319 series airplanes on which 

Airbus Mod 28238, Mod 28162, and Mod 

28342 have been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the holes of the upper cleat to upper stringer 

attachments at rib 2 through rib 7 of the leftand right-hand wings are subject to 

widespread fatigue damage. We are issuing 

this AD to prevent fatigue cracking in the 

stringer attachment holes of the wings, which 

could result in reduced structural integrity of 

the wings. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Before reaching the upper limit, but not 

before reaching the lower limit, as defined in 

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

applicable: Modify the holes of the upper 

cleat to upper stringer attachments at rib 2 

through rib 7 inclusive, on the left- and righthand wings by oversizing the holes, doing 

eddy current inspections of the holes for 

damage, and repairing any damage found 

before further flight, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1208, dated 

November 21, 2016, except as required by 

paragraph (h) of this AD; or using a method 

approved by the Manager, International 

Section, Transport Standards Branch, 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. 


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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22357 

(h) Service Information Exception 

Where Airbus Service Bulletin A320–57– 

1208, dated November 21, 2016, specifies to 

contact Airbus for appropriate action, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance): Before further flight, 

accomplish corrective actions in accordance 

with the procedures specified in paragraph 

(i)(2) of this AD. 

(i) 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 (j)(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 paragraph (h) 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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0117, dated July 7, 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–2017–1245. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3223. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–57–1208, 

dated November 21, 2016. 

(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 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 

April 20, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. R1–2018–09280 Filed 5–14–18; 8:45 am] 

BILLING CODE 1301–00–P 


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