27724 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

BAE Systems (Operations) Limited: Docket 

No. FAA–2018–0511; Product Identifier 

2017–NM–145–AD. 

(a) Comments Due Date 

We must receive comments by July 30, 

2018. 

(b) Affected ADs 

This AD affects AD 2005–15–11, 

Amendment 39–14200 (70 FR 43025, July 26, 

2005) (‘‘AD 2005–15–11’’). 

(c) Applicability 

This AD applies to all BAE Systems 

(Operations) Limited Model 4101 airplanes, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that it is possible for cracks in fuselage frame 

90 to exceed the critical length for failure in 

less time than the current inspection interval; 

and a determination that inspection 

requirements for a number of maintenance 

tasks involving certain airworthiness 

limitations are incorrect. We are issuing this 

AD to address cracking in fuselage frame 90, 

which could cause it to fail and thereby 

compromise the structural integrity of the 

aircraft pressure hull. We are also issuing this 

AD to address fatigue damage of various 

airplane structures, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the compliance times specified in 

paragraphs (g)(1) and (g)(2) of this AD, as 

applicable: Do a detailed inspection of 

fuselage frame 90 for cracking or fatigue 

damage, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Alert Service 

Bulletin J41–A53–058, dated December 6, 

2016. If any cracking or fatigue damage is 

found: Before further flight, repair using a 

method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or BAE Systems 

(Operations) Limited’s EASA Design 

Organization Approval (DOA). 

(1) For airplanes with 6,300 flight cycles or 

fewer since Structural Significant Items (SSI) 

53–10–029 (Maintenance Planning Document 

(MPD) 531029–DVl–10010–1) was last 

accomplished: Within 6,600 flight cycles 

after the last accomplishment of SSI 53–10– 

029 (MPD 531029–DVl–10010–1), or within 6 

months after the effective date of this AD, 

whichever is later. 

(2) For airplanes with more than 6,300 

flight cycles since SSI 53–10–029 (MPD 

531029–DVl–10010–1) was last 

accomplished: Within 300 flight cycles or 4.5 

months, whichever is earlier, since the last 

accomplishment of SSI 53–10–029 (MPD 

531029–DVl–10010–1), or within 6 months 

after the effective date of this AD, whichever 

is later. 

(h) Maintenance or Inspection Program 

Revisions 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the maintenance tasks and 

associated thresholds and intervals described 

in, and in accordance with, the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–51–001, Revision 4, dated July 

11, 2017, as applicable. The initial 

compliance times for new or revised tasks are 

at the applicable times specified in BAE 

Systems (Operations) Limited Service 

Bulletin J41–51–001, Revision 4, dated July 

11, 2017, or within 6 months after the 

effective date of this AD, whichever is later. 

(i) No Alternative Actions and Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (h) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l)(1) of 

this AD. 

(j) Terminating Action for Requirements of 

AD 2005–15–11 

Accomplishment of the actions required by 

paragraph (h) of this AD terminates all 

requirements of AD 2005–15–11. 

(k) No Reporting Requirement 

Although the Accomplishment Instructions 

of BAE Systems (Operations) Limited Alert 

Service Bulletin J41–A53–058, dated 

December 6, 2016, specify to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(l) 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 (m)(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: 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 the 

European Aviation Safety Agency (EASA); or 

BAE Systems (Operations) Limited’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0187, dated September 22, 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–2018–0511. 

(2) For more information about this AD, 

contact Todd Thompson, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3228. 

(3) For service information identified in 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@

baesystems.com; internet http://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 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. 

Issued in Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12732 Filed 6–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0512; Product 

Identifier 2017–NM–170–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A318, A319, A320 and 

A321 series airplanes. This AD requires 

revising the maintenance or inspection 


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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27725 

program to incorporate new or more 

restrictive airworthiness limitations. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

indicating that the principal structural 

elements and certain life-limited parts 

are subject to widespread fatigue 

damage (WFD). We are proposing this 

AD to address the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by July 30, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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 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. 

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– 

0512; 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 NPRM, 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. Comments will be available in 

the AD docket shortly after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0512; Product Identifier 2017– 

NM–170–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM based 

on 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 NPRM. 

Discussion 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Widespread damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-site 

damage and multiple-element damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane. This 

condition is known as widespread 

fatigue damage. It is associated with 

general degradation of large areas of 

structure with similar structural details 

and stress levels. As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

This AD was prompted by an 

evaluation by the DAH indicating that 

the principal structural elements and 

certain life-limited parts are subject to 

WFD. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2017–0231, dated November 

21, 2017 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318, A319, A320 and A321 

series airplanes. The MCAI states: 

The airworthiness limitations for the A320 

family aeroplanes are currently defined and 

published in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitations Section 

(ALS) document(s). The Damage Tolerant 

Airworthiness Limitation Items are published 

in ALS Part 2, approved by EASA. The 

instructions contained in the ALS Part 2 have 

been identified as mandatory actions for 

continued airworthiness. 

Failure to comply with these instructions 

could result in an unsafe condition. 

Previously, EASA issued AD 2016–0239 

[which corresponds to FAA AD 2017–22–03, 

Amendment 39–19083 (82 FR 49091, October 

24, 2017) (‘‘AD 2017–22–03’’)] to require 

accomplishment of all maintenance tasks as 

described in ALS Part 2 at Revision 05, and 

[EASA] AD 2015–0038 (later revised) [which 

corresponds to FAA AD 2016–09–06, 

Amendment 39–18504 (81 FR 26113, May 2, 

2016) (‘‘AD 2016–09–06’’)] to require the 

implementation of reduced thresholds and 

intervals for the detailed inspection of the 

forward engine mount on both right hand 

and left hand sides of aeroplanes equipped 

with CFM56–5A/5B engines, as specified in 

the ALS task 712111–01. 

Since those [EASA] ADs were issued, 

Airbus published Revision 06 of the ALS Part 


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2, and variations up to 6.3, including new 

and/or more restrictive items, and new A320 

family models were certified and added to 

the Applicability of the ALS. The ALS Part 

2 Revision 06 also includes the reduced 

threshold and intervals required by EASA 

AD 2015–0038R1. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2016–0239 and EASA AD 2015–0038R1, 

which are superseded, requires 

accomplishment of all maintenance tasks as 

described in the ALS Part 2 Revision 06, and 

ALS Part 2 variations 6.1, 6.2 and 6.3 

(hereafter collectively referred to as ‘‘the 

ALS’’ in this [EASA] AD), and maintains 

specific compliance times for ALS task 

572021–01–1 (Wide Spread Fatigue Damage 

related). 

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– 

0512. 

Relationship Between Proposed AD, AD 

2016–09–06 and AD 2017–22–03 

This NPRM would not supersede AD 

2016–09–06 and AD 2017–22–03. 

Rather, we have determined that a 

stand-alone AD would be more 

appropriate to address the changes in 

the MCAI. This NPRM would require 

revising the maintenance or inspection 

program to incorporate new or more 

restrictive airworthiness limitations. 

Accomplishment of the proposed 

actions would then terminate the 

requirements of paragraphs (g) and (j) of 

AD 2016–09–06. Accomplishment of the 

proposed actions would also terminate 

paragraphs (g)(2) and (i) of 2017–22–03. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued A318/A319/A320/ 

A321 Airworthiness Limitation Section 

Part 2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Revision 06, 

dated April 10, 2017. The service 

information describes new or more 

restrictive airworthiness limitations. 

Airbus has also issued the following 

variations to A318/A319/A320/A321 

Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT—ALI), Revision 

06, dated April 10, 2017. 

• A318/A319/A320/A321 

Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Variation 

6.1, dated May 18, 2017. The service 

information describes ALI tasks 

applicable to certain Model A320–200 

and A321–200 airplane configurations. 

• A318/A319/A320/A321 

Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Variation 

6.2, dated May 24, 2017. The service 

information describes ALI tasks 

applicable to Model A321–271N and 

–272N airplanes. 

• A318/A319/A320/A321 

Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Variation 

6.3, October 24, 2017. The service 

information describes ALI tasks 

associated with door stops for certain 

Model A318, A319, A320, and A321 

series airplanes. 

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 Proposed 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 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (j)(1) of this proposed AD. 

The request should include a 

description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

Differences Between This Proposed AD 

and the MCAI 

The MCAI specifies that if there are 

findings from the airworthiness 

limitations section (ALS) inspection 

tasks, corrective actions must be 

accomplished in accordance with 

Airbus maintenance documentation. 

However, this proposed AD does not 

include that requirement. Operators of 

U.S.-registered airplanes are required by 

general airworthiness and operational 

regulations to perform maintenance 

using methods that are acceptable to the 

FAA. We consider those methods to be 

adequate to address any corrective 

actions necessitated by the findings of 

ALS inspections required by this 

proposed AD. 

Airworthiness Limitations Based on 

Type Design 

The FAA recently became aware of an 

issue related to the applicability of ADs 

that require incorporation of an ALS 

revision into an operator’s maintenance 

or inspection program. 

Typically, when these types of ADs 

are issued by civil aviation authorities 

of other countries, they apply to all 

airplanes covered under an identified 

type certificate (TC). The corresponding 

FAA AD typically retains applicability 

to all of those airplanes.In addition, U.S. 

operators must operate their airplanes in 

an airworthy condition, in accordance 

with 14 CFR 91.7(a). Included in this 

obligation is the requirement to perform 

any maintenance or inspections 

specified in the ALS, and in accordance 

with the ALS as specified in 14 CFR 

43.16 and 91.403(c), unless an 

alternative has been approved by the 

FAA. 

When a type certificate is issued for 

a type design, the specific ALS, 

including revisions, is a part of that type 

design, as specified in 14 CFR 21.31(c). 

The sum effect of these operational 

and maintenance requirements is an 

obligation to comply with the ALS 

defined in the type design referenced in 

the manufacturer’s conformity 

statement. This obligation may 

introduce a conflict with an AD that 

requires a specific ALS revision if new 

airplanes are delivered with a later 

revision as part of their type design. 

To address this conflict, the FAA has 

approved alternative methods of 

compliance (AMOCs) that allow 

operators to incorporate the most recent 

ALS revision into their maintenance/ 

inspection programs, in lieu of the ALS 

revision required by the AD. This 

eliminates the conflict and enables the 

operator to comply with both the AD 

and the type design. 

However, compliance with AMOCs is 

normally optional, and we recently 

became aware that some operators 

choose to retain the AD-mandated ALS 

revision in their fleet-wide 

maintenance/inspection programs, 

including those for new airplanes 

delivered with later ALS revisions, to 

help standardize the maintenance of the 

fleet. To ensure that operators comply 

with the applicable ALS revision for 

newly delivered airplanes containing a 

later revision than that specified in an 

AD, we plan to limit the applicability of 


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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27727 

ADs that mandate ALS revisions to 

those airplanes that are subject to an 

earlier revision of the ALS, either as part 

of the type design or as mandated by an 

earlier AD. 

This proposed AD therefore applies to 

certain Model Airbus Model A318, 

A319, A320 and A321 series airplanes 

with an original certificate of 

airworthiness or original export 

certificate of airworthiness that was 

issued on or before the date of approval 

of the ALS revision identified in this 

proposed AD. Operators of airplanes 

with an original certificate of 

airworthiness or original export 

certificate of airworthiness issued after 

that date must comply with the 

airworthiness limitations specified as 

part of the approved type design and 

referenced on the type certificate data 

sheet. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,180 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleet(s), we 

have determined that a per-operator 

estimate is more accurate than a perairplane estimate. Therefore, we 

estimate the total cost per operator to be 

$7,650 (90 work-hours × $85 per workhour). 

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 proposed 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2018–0512; Product 

Identifier 2017–NM–170–AD. 

(a) Comments Due Date 

We must receive comments by July 30, 

2018. 

(b) Affected ADs 

This AD affects AD 2016–09–06, 

Amendment 39–18504 (81 FR 26113, May 2, 

2016) (‘‘AD 2016–09–06’’) and AD 2017–22– 

03, Amendment 39–19083 (82 FR 49091, 

October 24, 2017) (‘‘AD 2017–22–03’’). 

(c) Applicability 

This AD applies to all Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD; certificated in any 

category; with an original certificate of 

airworthiness or original export certificate of 

airworthiness issued on or before October 24, 

2017. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, –233, –251N, and –271N 

airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, –232, –251N, –253N, 271N, 

and –272N airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder, which indicates 

that principal structural elements and certain 

life-limited parts are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to prevent fatigue cracking, accidental 

damage, or corrosion in principal structural 

elements, and WFD, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) New Maintenance or Inspection Program 

Revision 

(1) Within 90 days after the effective date 

of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the airworthiness limitations 

(ALIs) specified in Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Revision 06, 

dated April 10, 2017; and A318/A319/A320/ 

A321 Airworthiness Limitation Section Part 

2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Variation 6.3, 

October 24, 2017. Except for ALIs identified 

in paragraphs (g)(2) and (g)(3) of this AD, the 

initial compliance time for accomplishing the 

actions is at the applicable time identified in 

the ALIs specified in Airbus A318/A319/ 

A320/A321 Airworthiness Limitation Section 

Part 2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Revision 06, 

dated April 10, 2017; A318/A319/A320/A321 

Airworthiness Limitation Section Part 2— 

Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Variation 6.3, October 24, 

2017; or within 90 days after the effective 

date of this AD, whichever occurs later; 

without exceeding the inspection intervals in 


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27728 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 

the ALIs required by paragraph (i) of AD 

2017–22–03. 

(2) For airplanes identified in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Section Part 2—Damage Tolerant 

Airworthiness Limitation Items (DT–ALI), 

Variation 6.1, dated May 18, 2017: 

Concurrently with the revision required by 

paragraph (g)(1) of this AD, revise the 

maintenance or inspection program, as 

applicable, to incorporate the ALIs specified 

in Airbus A318/A319/A320/A321 

Airworthiness Limitation Section Part 2— 

Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Variation 6.1, dated May 18, 

2017. The initial compliance time for 

accomplishing the actions is at the applicable 

time identified in the ALIs specified in 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Section Part 2— 

Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Variation 6.1, dated May 18, 

2017, or within 90 days after the effective 

date of this AD, whichever occurs later; 

without exceeding the inspection intervals in 

the ALIs required by paragraph (i) of AD 

2017–22–03. 

(3) For airplanes identified in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Section Part 2—Damage Tolerant 

Airworthiness Limitation Items (DT–ALI), 

Variation 6.2, dated May 24, 2017: 

Concurrently with the revision required by 

paragraph (g)(1) of this AD, revise the 

maintenance or inspection program, as 

applicable, to incorporate the ALIs specified 

in A318/A319/A320/A321 Airworthiness 

Limitation Section Part 2—Damage Tolerant 

Airworthiness Limitation Items (DT–ALI), 

Variation 6.2, dated May 24, 2017. The initial 

compliance time for accomplishing the 

actions is at the applicable time identified in 

the ALIs specified in Airbus A318/A319/ 

A320/A321 Airworthiness Limitation Section 

Part 2—Damage Tolerant Airworthiness 

Limitation Items (DT–ALI), Variation 6.2, 

dated May 24, 2017, or within 90 days after 

the effective date of this AD, whichever 

occurs later; without exceeding the 

inspection intervals in the ALIs required by 

paragraph (i) of AD 2017–22–03. 

(h) No Alternative Actions, Intervals, and 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(i) Terminating Action for Other FAA ADs 

(1) Accomplishing the action required by 

paragraph (g) of this AD terminates the 

requirements of paragraphs (g) and (j) of AD 

2016–09–06. 

(2) Accomplishing the action required by 

paragraph (g) of this AD terminates the 

requirements of paragraphs (g)(2) and (i) of 

AD 2017–22–03. 

(j) 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 (k)(2) of this AD. Information may 

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

(ii) AMOCs previously approved for AD 

2015–05–02, Amendment 39–18112 (80 FR 

15152, March 23, 2015) that required 

incorporation of the service information in 

paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), 

(j)(1)(ii)(C), or (j)(1)(ii)(D), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(A) Airbus A318/A319/A320/A321 

Airworthiness Limitation Section Part 2— 

Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Revision 06, dated April 10, 

2017. 

(B) Airbus A318/A319/A320/A321 

Airworthiness Limitation Section Part 2— 

Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Variation 6.1, dated May 18, 

2017. 

(C) Airbus A318/A319/A320/A321 

Airworthiness Limitation Section Part 2 

–Damage Tolerant Airworthiness Limitation 

Items (DT–ALI), Variation 6.2, dated May 24, 

2017. 

(D) A318/A319/A320/A321 Airworthiness 

Limitation Section Part 2—Damage Tolerant 

Airworthiness Limitation Items (DT–ALI), 

Variation 6.3, October 24, 2017. 

(2) Contacting the Manufacturer: 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 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0231, dated November 21, 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–2018–0512. 

(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. 

(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. 

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. 

Issued in Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12733 Filed 6–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

SOCIAL SECURITY ADMINISTRATION 

20 CFR Part 401 

[Docket No. SSA–2015–0003] 

RIN 0960–AI08 

Social Security Administration 

Violence Evaluation and Reporting 

System 

AGENCY: Social Security Administration. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: In today’s Federal Register, 

the Social Security Administration 

(SSA) separately published, notice of a 

new system of records, Social Security 

Administration Violence Evaluation and 

Reporting System (SSAvers). Because 

this system will contain investigatory 

material compiled for law enforcement 

purposes, this proposed rule will 

exempt those records from specific 

provisions of the Privacy Act. 

DATES: To ensure that your comments 

are considered, we must receive them 

no later than July 16, 2018. 

ADDRESSES: You may submit comments 

by any one of three methods—internet, 

fax, or mail. Do not submit the same 

comments multiple times or by more 

than one method. Regardless of which 

method you choose, please state that 

your comments refer to Docket No. 

SSA–2015–0003, so that we may 

associate your comments with the 

correct regulation. 

Caution: You should be careful to 

include in your comments only 

information that you wish to make 

publicly available. We strongly urge you 

not to include in your comments any 

personal information, such as Social 

Security numbers or medical 

information. 

1. Internet: We strongly recommend 

that you submit your comments via the 

internet. Please visit the Federal 

eRulemaking portal at http:// 


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