Federal Register / Vol. 83, No. 119 / Wednesday, June 20, 2018 / Proposed Rules 28555 

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): 

Bombardier, Inc.: Docket No. FAA–2018– 

0546; Product Identifier 2017–NM–171– 

AD. 

(a) Comments Due Date 

We must receive comments by August 6, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc., 

Model BD–700–1A10 and BD–700–1A11 

airplanes, certificated in any category, serial 

numbers 9002 through 9770 inclusive, 9772 

through 9781 inclusive, and 9998. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

multiple in-flight departures of the aft belly 

fairing access panels. We are issuing this AD 

to prevent in-flight departures of the aft belly 

fairing access panels, which could result in 

runway hazards or hazards to people on the 

ground. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Access Panel Modification 

Within 15 months after the effective date 

of this AD, modify the aft belly fairing access 

panels by replacing the attachments, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraphs (g)(1) 

and (g)(2) of this AD. 

(1) For Model BD–700–1A10 airplanes: 

Bombardier Service Bulletin 700–53–050, or 

700–53–6008, both Revision 01, both dated 

December 16, 2016. 

(2) For Model BD–700–1A11 airplanes: 

Bombardier Service Bulletin 700–1A11–53– 

025, or 700–53–5009, both Revision 01, both 

dated December 16, 2016. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the applicable service 

information identified in paragraphs (h)(1) 

through (h)(4) of this AD. 

(1) Bombardier Service Bulletin 700– 

1A11–53–025, dated July 14, 2016. 

(2) Bombardier Service Bulletin 700–53– 

050, dated July 14, 2016. 

(3) Bombardier Service Bulletin 700–53– 

5009, dated July 14, 2016. 

(4) Bombardier Service Bulletin 700–53– 

6008, dated July 14, 2016. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2017–31, 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–2018–0546. 

(2) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

Airframe and Mechanical Systems Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7330; fax 516–794–5531. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; internet http://

www.bombardier.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 

8, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13126 Filed 6–19–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0556; Product 

Identifier 2018–NM–015–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 all 

Airbus Model A318 series; Model A319 

series; Model A320 series; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. This 

proposed AD was prompted by reports 

of multiple angle of attack (AoA) probe 

blockages. This proposed AD would 

require all elevator aileron computer 

(ELAC) units to be upgraded with new 

software, or replaced with upgraded 

units. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by August 6, 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. 


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• 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– 

0556; 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 206–231–3223; fax 206–231– 

3398. 

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– 

2018–0556; Product Identifier 2018– 

NM–015–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018– 

0007R1, dated January 19, 2018 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318 

series; Model A319 series; Model A320 

series; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes. The MCAI states: 

Occurrences were reported on multiple 

Angle of Attack (AoA) probes blockages. 

Investigation results indicated the need for 

improved AoA monitoring in order to detect 

cases of AoA probe blockage. 

This condition, if not corrected, could lead 

to undue activation of the AoA protection, 

reverting to manual control of the aeroplane, 

which, under specific circumstances, could 

result in reduced control of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed several Elevator Aileron 

Computer (ELAC) standards, i.e. ELAC units 

loaded with a specific software Part Number 

(P/N), and EASA issued AD 2017–0008, 

retaining part of the requirements of EASA 

AD 2015–0088R1 [which corresponds to FAA 

AD 2016–17–03, Amendment 39–18616 (81 

FR 55358, August 19, 2016) (‘‘AD 2016–17– 

03’’)], which was superseded, and requiring 

an upgrade of all ELAC units with ELAC L99 

standard, which introduces improvements in 

the AoA probe monitoring for Current Engine 

Option (CEO) aeroplanes, and also 

incorporates flight control aspects for New 

Engine Option (NEO) aeroplanes. 

Since that [EASA] AD was issued, it was 

determined that clarification is necessary for 

the Parts Installation requirements, and some 

typographical (P/N) errors were detected. 

This [EASA] AD is revised accordingly. 

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– 

0556. 

Relationship of Proposed AD to AD 

2016–17–03 

This NPRM does not propose to 

supersede AD 2016–17–03. Rather, we 

have determined that a stand-alone AD 

would be more appropriate to address 

the changes in the MCAI. This proposed 

AD would require all ELAC units to be 

upgraded with new software, or 

replaced with upgraded units. 

Accomplishment of the proposed 

actions would then terminate all of the 

requirements of AD 2016–17–03. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–27–1263, Revision 00, dated April 

28, 2017; and Service Bulletin A320– 

27–1264, Revision 00, dated April 28, 

2017. The service information describes 

the upgrade or replacement of ELAC 

units. These documents are distinct 

because they apply to different airplane 

configurations. 

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 the same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,250 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Modification ................ 3 work-hours × $85 per hour = $255 ............. Up to $7,970 .............. Up to $8,225 .............. Up to $10,281,250 

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. 


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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–2018–0556; Product 

Identifier 2018–NM–015–AD. 

(a) Comments Due Date 

We must receive comments by August 6, 

2018. 

(b) Affected ADs 

This AD affects AD 2016–17–03, 

Amendment 39–18616 (81 FR 55358, August 

19, 2016) (‘‘AD 2016–17–03’’). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(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, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

multiple angle of attack (AoA) probe 

blockages. We are issuing this AD to address 

the blockage of AoA probes. This condition, 

if not corrected, could lead to undue 

activation of the AoA protection, reverting to 

manual control of the airplane, which, under 

specific circumstances, could result in 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected Elevator Aileron 

Computer (ELAC) 

For the purposes of this AD, ELAC units 

having a part number (P/N) listed in table 1 

to paragraphs (g), (h), and (i) of this AD are 

hereafter referred to as ‘‘affected ELAC’’ in 

this AD. 

BILLING CODE 4910–13–P 


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sradovich on DSK3GMQ082PROD with PROPOSALSEP20JN18.000</GPH>

Table 1 to paragraphs (g), (h), and (i) of this AD- Affected ELAC Part Numbers 

ELACP/N Designation FIN 

3945122202 ELAC A320-111 Type Def. 2 CE 1 I 2 

3945122203 ELACL50C 2 CE 1 I 2 

3945122303 ELACL50C 2 CE 1 I 2 

3945122304 ELACL60 2 CE 1 I 2 

3945122305 ELACL61B 2 CE 1 I 2 

3945122306 ELACL61F 2 CE 1 I 2 

3945122307 ELACL62C 2 CE 1 I 2 

C12370AA01 ELACL68C 2 CE 1 I 2 

3945122501 ELACL69 2 CE 1 I 2 

3945122502 ELAC L69J 2 CE 1 I 2 

3945122503 ELACL77 2 CE 1 I 2 

3945122504 ELACL78 2 CE 1 I 2 

3945122505 ELAC AL80 2 CE 1 I 2 

3945123505 ELAC A' L80 2 CE 1 I 2 

3945128101 ELACBL80 2 CE 1 I 2 

3945122506 ELAC AL81 2 CE 1 I 2 

3945123506 ELAC A' L81 2 CE 1 I 2 

3945128102 ELAC B L81 2 CE 1 I 2 

3945122507 ELAC AL82 2 CE 1 I 2 

3945123507 ELAC A' L82 2 CE 1 I 2 

3945128103 ELACBL82 2 CE 1 I 2 

3945122608 ELAC AL83 2 CE 1 I 2 

3945123608 ELAC A' L83 2 CE 1 I 2 

3945122609 ELAC AL84 2 CE 1 I 2 

3945123609 ELAC A' L84 2 CE 1 I 2 

3945128204 ELACBL90L 2 CE 1 I 2 

3945128205 ELACBL90N 2 CE 1 I 2 

3945128206 ELACBL91 2 CE 1 I 2 

3945129101 ELAC B L91 data loadable 2 CE 1 I 2 SW1 

3945128207 ELACBL92 2 CE 1 I 2 

3945128208 ELACBL92L 2 CE 1 I 2 

3945128209 ELACBL93 2 CE 1 I 2 

3945129103 ELAC B L93 data loadable 2 CE 1 I 2 SW1 

3945128210 ELACBL94 2 CE 1 I 2 
Federal Register / Vol. 83, No. 119 / Wednesday, June 20, 2018 / Proposed Rules 28559 

BILLING CODE 4910–13–C 

(h) Required Actions 

For airplanes with ELAC part numbers 

listed in table 1 to paragraphs (g), (h), and (i) 

of this AD: Within the applicable compliance 

times defined in figure 1 to paragraph (h) of 

this AD, upgrade each ELAC by uploading 

L99 software part number (P/N) 3945129111 

or by replacing the existing ELAC with ELAC 

L99 P/N 3945128217 in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1263, Revision 00, 

dated April 28, 2017, or Airbus Service 

Bulletin A320–27–1264, Revision 00, dated 

April 28, 2017, as applicable, or in 

accordance with modification instructions 

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); or in 

accordance with modification instructions 

approved by an EASA DOA (other than the 

Airbus EASA DOA), provided the conditions 

specified in paragraphs (h)(1) through (h)(4) 

of this AD are met. If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(1) Absence of electronic centralized 

aircraft monitoring (ECAM) warning or 

maintenance message related to ELAC, before 

the data-loadable ELAC unit is removed and 

software is loaded. 

(2) The data-loadable ELAC unit is 

removed as specified in Airbus aircraft 

maintenance manual (AMM) Task 27–93–34– 

000–001–A. 

(3) The data-loadable ELAC unit is checked 

by two different means, either line 

replaceable unit (LRU) identification and 

label call up, or Alpha Call Up ELA 1 and 

ELA 2. 

(4) After the software is loaded, the dataloadable ELAC unit is re-installed as 

specified in Airbus AMM Task 27–93–34– 

400–001–A. 

Note 1 to paragraph (h) of this AD: Nondata-loadable ELAC L99 P/N 3945128217 

units are fully interchangeable and mixable 

with data-loadable ELAC L99 P/N 

3945129100 units with L99 software P/N 

3945129111 loaded. 

(i) Parts Installation Prohibition 

(1) For airplanes with ELAC units listed in 

table 1 to paragraphs (g), (h), and (i) of this 

AD: After modification of an airplane as 

required by paragraph (h) of this AD, do not 

install any affected ELAC on that airplane. 

(2) For airplanes with ELAC units not 

listed in table 1 to paragraphs (g), (h), and (i) 

of this AD: From the effective date of this AD, 

do not install any affected ELAC on that 

airplane. 

(j) Installation of Later Software Versions 

Installation of an ELAC unit with a 

software standard above L99 is equal to 

compliance with the requirements of 

paragraph (h) of this AD, provided the 

conditions specified in paragraphs (j)(1) 

through (j)(2) of this AD are met. 

(1) The ELAC unit part number is approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus’s EASA DOA. 

(2) The installation is accomplished in 

accordance with modification instructions 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus’s EASA DOA; or in 

accordance with modification instructions 

approved by an EASA DOA (other than the 

Airbus EASA DOA), provided the conditions 

in paragraphs (j)(2)(i) through (j)(2)(iv) of this 

AD are met. 

(i) Absence of ECAM warning or 

maintenance message related to ELAC, before 

the data-loadable ELAC unit is removed and 

software is loaded. 

(ii) The data-loadable ELAC unit is 

removed as specified in Airbus AMM Task 

27–93–34–000–001–A. 

(iii) The data-loadable ELAC unit is 

checked by two different means, either LRU 

identification and label call up, or Alpha Call 

Up ELA 1 and ELA 2. 

(iv) After the software is loaded, the dataloadable ELAC unit is re-installed as 

specified in Airbus AMM Task 27–93–34– 

400–001–A. 

(k) Airplanes Not Affected by the 

Requirements of Paragraph (h) of This AD 

(1) An airplane on which any modification 

(mod) specified in paragraphs (k)(1)(i) and 

(k)(1)(ii) of this AD was embodied in 

production is not affected by the 

requirements of paragraph (h) of this AD, 

provided it is determined that no affected 

ELAC is installed as of the effective date of 

this AD. 

(i) Airbus mod 161843 (installation of dataloadable ELAC P/N 3945129100 unit with 

L99 software P/N 3945129111) or mod 


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159979 (installation of non-data-loadable 

ELAC L99 P/N 3945128217). 

(ii) Airbus mod 160577 (installation of 

data-loadable ELAC P/N 3945129100 unit 

with L101 software P/N 3945129112) or mod 

162042 (installation of non-data-loadable 

ELAC L101 P/N 3945128218). 

(2) An airplane on which any modification 

specified in paragraphs (k)(2)(i), (k)(2)(ii), or 

(k)(2)(iii) of this AD was done is not affected 

by the requirements of paragraph (h) of this 

AD, provided it is determined that no 

affected ELAC is installed as of the effective 

date of this AD. 

(i) A modification specified in Airbus 

Service Bulletin A320–27–1267, Revision 00, 

dated September 27, 2017 (ELAC L101 P/N 

3945128218 non-data-loadable). 

(ii) A modification specified in Airbus 

Service Bulletin A320–27–1268, Revision 00, 

dated September 27, 2017 (ELAC P/N 

3945129100 data-loadable with L101 

software P/N 3945129112 for A320 NEO). 

(iii) A modification specified in Airbus 

Service Bulletin A320–27–1269, Revision 00, 

dated September 27, 2017 (ELAC P/N 

3945129100 data-loadable with L101 

software P/N 3945129112). 

(l) Terminating Action for AD 2016–17–03 

Accomplishing the actions required by 

paragraph (h) of this AD or complying with 

any method of compliance specified in 

paragraph (k) of this AD terminates all 

requirements of AD 2016–17–03. 

(m) 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 (n)(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 EASA; 

or Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0007R1, dated January 19, 2018, 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–2018–0556. 

(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 206–231– 

3223; fax 206–231–3398. 

(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. 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 

7, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12885 Filed 6–19–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOUSING AND 

URBAN DEVELOPMENT 

24 CFR Part 100 

[Docket No. FR–6111–A–01] 

RIN 2529–ZA01 

Reconsideration of HUD’s 

Implementation of the Fair Housing 

Act’s Disparate Impact Standard 

AGENCY: Office of the Assistant 

Secretary for Fair Housing and Equal 

Opportunity, HUD. 

ACTION: Advance notice of proposed 

rulemaking. 

SUMMARY: This advance notice of 

proposed rulemaking (ANPR) invites 

public comment on possible 

amendments to HUD’s 2013 final rule 

implementing the Fair Housing Act’s 

disparate impact standard, as well as the 

2016 supplement to HUD’s responses to 

certain insurance industry comments 

made during the rulemaking. HUD is 

reviewing the final rule and supplement 

to determine what changes, if any, are 

appropriate following the Supreme 

Court’s 2015 ruling in Texas 

Department of Housing and Community 

Affairs v. Inclusive Communities 

Project, Inc., which held that disparate 

impact claims were cognizable under 

the Fair Housing Act and discussed 

standards for, and the constitutional 

limitations on, such claims. As HUD 

conducts its review, it is soliciting 

public comment on the disparate impact 

standard set forth in the final rule and 

supplement, the burden-shifting 

approach, the relevant definitions, the 

causation standard, and whether 

changes to these or other provisions of 

the rule would be appropriate. HUD is 

also issuing this ANPR in response to 

public comments submitted on its May 

15, 2017, Federal Register document 

seeking input on ineffective regulations 

and an October 26, 2017, 

recommendation from the Department 

of the Treasury. 

DATES: Comment Due Date: August 20, 

2018. 

ADDRESSES: Interested persons are 

invited to submit comments to the 

Office of the General Counsel, Rules 

Docket Clerk, Department of Housing 

and Urban Development, 451 Seventh 

Street SW, Room 10276, Washington, 

DC 20410–0001. Communications 

should refer to the above docket number 

and title and should contain the 

information specified in the ‘‘Request 

for Comments’’ section. There are two 

methods for submitting public 

comments. 

1. Submission of Comments by Mail. 

Comments may be submitted by mail to 

the Regulations Division, Office of 

General Counsel, Department of 

Housing and Urban Development, 451 

7th Street SW, Room 10276, 

Washington, DC 20410–0500. Due to 

security measures at all federal agencies, 

however, submission of comments by 

mail often results in delayed delivery. 

To ensure timely receipt of comments, 

HUD recommends that comments 

submitted by mail be submitted at least 

two weeks in advance of the public 

comment deadline. 

2. Electronic Submission of 

Comments. Interested persons may 

submit comments electronically through 

the Federal eRulemaking Portal at 

http://www.regulations.gov. HUD 

strongly encourages commenters to 

submit comments electronically. 

Electronic submission of comments 

allows the commenter maximum time to 

prepare and submit a comment, ensures 

timely receipt by HUD, and enables 

HUD to make comments immediately 

available to the public. Comments 

submitted electronically through the 

http://www.regulations.gov website can 

be viewed by other commenters and 

interested members of the public. 

Commenters should follow instructions 

provided on that site to submit 

comments electronically. 

Note: To receive consideration as public 

comments, comments must be submitted 

through one of the two methods specified 


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