Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 26877 

allocate an amount of leverage to Early 

Stage SBICs on an annual basis. Other 

comments suggested concerns or 

requested clarifications. It was not 

evident to SBA from these comments 

that the proposed rule was broadly 

supported by SBIC program 

stakeholders. 

The withdrawal of the proposed rule 

does not impact the Early Stage 

regulations contained in 13 CFR part 

107 or the five currently licensed Early 

Stage SBICs. Such Early Stage SBICs 

remain subject to the Act, applicable 

regulations at 13 CFR part 107 and SBA 

policies. 

Executive Order 13771 

The withdrawal of the proposed rule 

qualifies as a deregulatory action under 

Executive Order 13771. See OMB’s 

Memorandum titled ‘‘Guidance 

Implementing Executive Order 13771, 

Titled ‘Reducing Regulation and 

Controlling Regulatory Costs’’’ (April 5, 

2017). 

Accordingly, for the reasons stated in 

the preamble, the proposed rule 

published at 81 FR 64075 on September 

16, 2016 is withdrawn. 

Authority: 15 U.S.C. 634(b)(6). 

Dated: May 12, 2018. 

Linda E. McMahon, 

Administrator. 

[FR Doc. 2018–12030 Filed 6–8–18; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0509; Product 

Identifier 2017–NM–076–AD] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

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 

Embraer S.A. Model ERJ 190 airplanes. 

This proposed AD was prompted by 

reports of bushing migration and loss of 

nut torque on the engine pylon lower 

inboard and outboard link fittings. This 

proposed AD would require 

modification of the attaching parts of 

the left-hand (LH) and right-hand (RH) 

pylon lower link fittings, inboard and 

outboard positions. We are proposing 

this AD to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by July 26, 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 Embraer S.A., 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—Brazil; telephone: +55 12 

3927–5852 or +55 12 3309–0732; fax: 

+55 12 3927–7546; email: distrib@

embraer.com.br; internet: http://

www.flyembraer.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– 

0509; 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: 

Krista Greer, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3221. 

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– 

2018–0509; Product Identifier 2017– 

NM–076–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 

Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC), which is the aviation authority 

for Brazil, has issued Brazilian AD 

2017–04–01, effective April 25, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Embraer S.A. 

Model ERJ 190 airplanes. The MCAI 

states: 

This [Brazilian] AD was prompted by 

reports of bushing migration and loss of nut 

torque on the engine pylon lower inboard 

and outboard link fittings. We are issuing this 

[Brazilian] AD to prevent loss of integrity of 

the engine pylon lower link fittings, which 

could result in separation of the engine from 

the wing. 

This [Brazilian] AD requires modifications 

of the attaching parts of the left handle (LH) 

and right handle (RH) pylon lower link 

fittings, inboard and outboard positions. 

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– 

0509. 

Related Service Information Under 1 

CFR Part 51 

Embraer S.A. has issued Embraer 

Service Bulletin 190–54–0016, Revision 

04, dated December 7, 2017; and 

Embraer Service Bulletin 190LIN–54– 

0008, Revision 02, dated May 9, 2018. 

The service information describes 

procedures for modification of the 

attaching parts of the LH and RH pylon 

lower link fittings, inboard and 

outboard positions. These documents 

are distinct since they apply to different 

airplane models. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 


daltland on DSKBBV9HB2PROD with PROPOSALS
26878 Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 

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 85 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 ............ Up to 270 work-hours × $85 per hour = $22,950 .. $3,200 Up to $26,150 ................ Up to $2,222,750. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all available 

costs in our cost estimate. 

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): 

Embraer S.A.: Docket No. FAA–2018–0509; 

Product Identifier 2017–NM–076–AD. 

(a) Comments Due Date 

We must receive comments by July 26, 

2018. 

(b) Affected ADs 

This AD affects AD 2014–16–16, 

Amendment 39–17940 (79 FR 48018, August 

15, 2014) (‘‘AD 2014–16–16’’). 

(c) Applicability 

This AD applies to the Embraer S.A. 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model ERJ 190–100 STD, –100 LR, and 

–100 IGW airplanes; and Model ERJ 190–200 

STD, –200 LR, and –200 IGW airplanes; as 

identified in Embraer Service Bulletin 190– 

54–0016, Revision 04, dated December 7, 

2017. 

(2) Model ERJ 190–100 ECJ airplanes as 

identified in Embraer Service Bulletin 

190LIN–54–0008, Revision 02, dated May 9, 

2018. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by reports of 

bushing migration and loss of nut torque on 

the engine pylon lower inboard and outboard 

link fittings. We are issuing this AD to 

prevent loss of integrity of the engine pylon 

lower link fittings, and possibly resulting in 

separation of the engine from the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

(1) Group 1 airplanes are defined as: Serial 

numbers 19000002, 19000004, 19000006 

through 19000108 inclusive, 19000110 

through 19000139 inclusive, 19000141 

through 19000158 inclusive, 19000160 

through 19000176 inclusive, 19000178 

through 19000202 inclusive, 19000204 

through 19000224 inclusive, 19000226 

through 19000235 inclusive, 19000237 

through 19000242 inclusive, 19000244 

through 19000260 inclusive, 19000262 

through 19000277 inclusive, 19000279 

through 19000295 inclusive, 19000297 

through 19000306 inclusive, 19000308 

through 19000316 inclusive, 19000318 

through 19000361 inclusive, 19000363 

through 19000437 inclusive, 19000439 

through 19000452 inclusive, 19000454 

through 19000466 inclusive, 19000468 

through 19000525 inclusive, 19000527 

through 19000533 inclusive, 19000535 

through 19000558 inclusive, 19000560 

through 19000570 inclusive, 19000572 

through 19000610 inclusive, 19000612 

through 19000631 inclusive, and 19000633 

through 19000636 inclusive. 

(2) Group 2 airplanes are defined as: Serial 

numbers 19000637 through 19000640 

inclusive, 19000642 through 19000655 

inclusive, 19000657 through 19000682 

inclusive, 19000684 through 19000686 

inclusive, 19000688, 19000689, and 

19000692 through 19000694 inclusive. 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 26879 

(h) Left-Hand (LH) Pylon Lower Link Fitting 

Attaching Parts Modification 

(1) For Group 1 airplanes as identified in 

paragraph (g)(1) of this AD: Within 15,000 

flight hours or 48 months after the effective 

date of this AD, whichever occurs later, 

replace the plain bushings of the lower 

inboard and outboard link fittings, install the 

lock washers with the L-profile on the fuse 

pin’s head side, and replace the internal 

shear pin of the fuse pins with new ones 

having larger head diameter, in accordance 

with ‘‘PART I’’ of the Accomplishment 

Instructions of Embraer Service Bulletin 190– 

54–0016, Revision 04, dated December 7, 

2017. 

(2) For Group 2 airplanes as identified in 

paragraph (g)(2) of this AD: Within 15,000 

flight hours or 48 months after the effective 

date of this AD, whichever occurs later, 

replace the internal shear pin of the fuse pins 

with new ones having larger head diameter, 

in accordance with ‘‘PART I’’ of the 

Accomplishment Instructions of Embraer 

Service Bulletin 190–54–0016, Revision 04, 

dated December 7, 2017. 

(3) For airplanes identified as Group 1 in 

Embraer Service Bulletin 190LIN–54–0008, 

Revision 02, dated May 9, 2018: Within 48 

months after the effective date of this AD, 

replace the plain bushings of the lower 

inboard and outboard link fittings, install the 

lock washers with the L-profile on the fuse 

pin’s head side, and replace the internal 

shear pin of the fuse pins with new ones 

having larger head diameter, in accordance 

with ‘‘PART I’’ of the Accomplishment 

Instructions of Embraer Service Bulletin 

190LIN–54–0008, Revision 02, dated May 9, 

2018. 

(4) For airplanes identified as Group 2 in 

Embraer Service Bulletin Embraer Service 

Bulletin 190LIN–54–0008, Revision 02, dated 

May 9, 2018: Within 48 months after the 

effective date of this AD, replace the internal 

shear pin of the fuse pins with new ones 

having larger head diameter, in accordance 

with ‘‘PART I’’ of the Accomplishment 

Instructions of Embraer Service Bulletin 

190LIN–54–0008, Revision 02, dated May 9, 

2018. 

(i) Right-Hand (RH) Pylon Lower Link 

Fitting Attaching Parts Modification 

(1) For Group 1 airplanes as identified in 

paragraph (g)(1) of this AD: Within 15,000 

flight hours or 48 months after the effective 

date of this AD, whichever occurs later, 

replace the plain bushings of the lower 

inboard and outboard link fittings, install the 

lock washers with the L-profile on the fuse 

pin’s head side, and replace the internal 

shear pin of the fuse pins with new ones 

having larger head diameter, in accordance 

with ‘‘PART II’’ of the Accomplishment 

Instructions of Embraer Service Bulletin 190– 

54–0016, Revision 04, dated December 7, 

2017. 

(2) For Group 2 airplanes as identified in 

paragraph (g)(2) of this AD: Within 15,000 

flight hours or 48 months after the effective 

date of this AD, whichever occurs later, 

replace the internal shear pin of the fuse pins 

with new ones having larger head diameter, 

in accordance with ‘‘PART II’’ of the 

Accomplishment Instructions of Embraer 

Service Bulletin 190–54–0016, Revision 04, 

dated December 7, 2017. 

(3) For airplanes identified as Group 1 in 

Embraer Service Bulletin Embraer Service 

Bulletin 190LIN–54–0008, Revision 02, dated 

May 9, 2018: Within 48 months after the 

effective date of this AD, replace the plain 

bushings of the lower inboard and outboard 

link fittings, install the lock washers with the 

L-profile on the fuse pin’s head side, and 

replace the internal shear pin of the fuse pins 

with new ones having larger head diameter, 

in accordance with ‘‘PART II’’ of the 

Accomplishment Instructions of Embraer 

Service Bulletin 190LIN–54–0008, Revision 

02, dated May 9, 2018. 

(4) For airplanes identified as Group 2 in 

Embraer Service Bulletin Embraer Service 

Bulletin 190LIN–54–0008, Revision 02, dated 

May 9, 2018: Within 48 months after the 

effective date of this AD, replace the internal 

shear pin of the fuse pins with new ones 

having larger head diameter, in accordance 

with ‘‘PART II’’ of the Accomplishment 

Instructions of Embraer Service Bulletin 

190LIN–54–0008, Revision 02, dated May 9, 

2018. 

(j) Terminating Action for AD 2014–16–16 

(1) Accomplishing the actions required by 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g)(1), (h)(1), and (i)(1) of AD 

2014–16–16 for that LH pylon lower link 

fitting. 

(2) Accomplishing the actions required by 

paragraph (h)(3) or (h)(4) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g)(2), (h)(2), and (i)(2) of AD 

2014–16–16 for that LH pylon lower link 

fitting. 

(3) Accomplishing the actions required by 

paragraph (i)(1) or (i)(2) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g)(1), (h)(1), and (i)(1) of AD 

2014–16–16 for that RH pylon lower link 

fitting. 

(4) Accomplishing the actions required by 

paragraph (i)(3) or (i)(4) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g)(2), (h)(2), and (i)(2) of AD 

2014–16–16 for that RH pylon lower link 

fitting. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (h)(1), (h)(2), 

(i)(1), and (i)(2) of this AD, if those actions 

were performed before the effective date of 

this AD using Embraer Service Bulletin 190– 

54–0016, dated September 22, 2015; Embraer 

Service Bulletin 190–54–0016, Revision 01, 

dated January 18, 2016; Embraer Service 

Bulletin 190–54–0016, Revision 02, dated 

September 12, 2016; or Embraer Service 

Bulletin 190–54–0016, Revision 03, dated 

May 18, 2017. 

(2) This paragraph provides credit for 

actions required by paragraphs (h)(3), (h)(4), 

(i)(3), and (i)(4) of this AD, if those actions 

were performed before the effective date of 

this AD using Embraer Service Bulletin 

190LIN–54–0008, dated October 2, 2015; 

Embraer Service Bulletin 190LIN–54–0008, 

Revision 01, dated April 13, 2017. 

(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 

Ageˆncia Nacional de Aviac ̧a ̃o Civil (ANAC); 

or ANAC’s authorized Designee. If approved 

by the ANAC Designee, the approval must 

include the Designee’s authorized signature. 

(3) Required for Compliance (RC): For 

service information that contains steps that 

are labeled as RC, the provisions of 

paragraphs (l)(3)(i) and (l)(3)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

AD 2017–04–01, effective April 25, 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–2018–0509. 

(2) For more information about this AD, 

contact Krista Greer, Aerospace Engineer, 

International Section, Transport Standards 

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

Moines, WA 98198; telephone and fax 206– 

231–3221. 

(3) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—Brazil; telephone: +55 

12 3927–5852 or +55 12 3309–0732; fax: +55 

12 3927–7546; email: 


daltland on DSKBBV9HB2PROD with PROPOSALS
26880 Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 

distrib@embraer.com.br; internet: http://

www.flyembraer.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 May 

31, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12228 Filed 6–8–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0505; Product 

Identifier 2017–NM–178–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 A350–941 airplanes. This 

proposed AD was prompted by a report 

of an overheat failure mode of the 

hydraulic engine-driven pump, which 

could cause a fast temperature rise of 

the hydraulic fluid. This proposed AD 

would require modifying the hydraulic 

monitoring and control application 

(HMCA) software. We are proposing this 

AD to address the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by July 26, 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 SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

continued-airworthiness.a350@

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– 

0505; 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: 

Kathleen Arrigotti, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218. 

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– 

2018–0505; Product Identifier 2017– 

NM–178–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 2017–0200, 

dated October 10, 2017 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A350–941 

airplanes. The MCAI states: 

In the Airbus A350 design, the hydraulic 

fluid cooling system is located in the fuel 

tanks. Recently, an overheat failure mode of 

the hydraulic engine-driven pump (EDP) was 

found. Such EDP failure may cause a fast 

temperature rise of the hydraulic fluid. 

This condition, if not detected and 

corrected, combined with an inoperative fuel 

tank inerting system, could lead to an 

uncontrolled overheat of the hydraulic fluid, 

possibly resulting in ignition of the fuel-air 

mixture in the affected fuel tank. 

To address this potential unsafe condition, 

Airbus issued a Major Event Revision (MER) 

of the A350 Master Minimum Equipment List 

(MMEL) that incorporates restrictions to 

avoid an uncontrolled overheat of the 

hydraulic system. Consequently, EASA 

issued Emergency AD 2017–0154–E to 

require implementation of these dispatch 

restrictions. 

Since EASA Emergency AD 2017–0154–E 

was issued, following further investigation, 

Airbus issued another MER of the A350 

MMEL that expands the number of restricted 

MMEL items. At the same time, Airbus 

revised Flight Operation Transmission (FOT) 

999.0068/17, to inform all operators about 

the latest MMEL restrictions. Consequently, 

EASA issued AD 2017–0180, retaining the 

requirements of EASA Emergency AD 2017– 

0154–E, which was superseded, and 

requiring implementation of the new Airbus 

A350 MMEL MER and, consequently, 

restrictions for aeroplane dispatch. 

Since EASA AD 2017–0180 was issued, 

Airbus developed a software (SW) update of 

the Hydraulic Monitoring and Control 

Application (HMCA) SW S4.2, introduction 

of which avoids uncontrolled overheat of the 

hydraulic system. HMCA SW S4.2 is 

embodied in production through Airbus 

modification (mod) 112090, and introduced 

in service through Airbus Service Bulletin 

(SB) A350–29–P012. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2017–0180, which is superseded, and 

requires modification of the aeroplane by 

installing HMCA SW S4.2. 

This [EASA] AD is still considered to be 

an interim action and further AD action may 

follow. 

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– 

0505. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A350–29–P012, dated October 6, 2017. 

The service information describes 

procedures for modifying the HMCA 

software by installing HMCA software 

S4.2 upgrades. 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. 


daltland on DSKBBV9HB2PROD with PROPOSALS