Airworthiness Directives; Embraer S.A. Airplanes, 26877-26880 [2018-12228]
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Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules
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16, 2016 is withdrawn.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
Examining the AD Docket
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
daltland on DSKBBV9HB2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:25 Jun 08, 2018
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
https://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 Sao 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: https://
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.
Jkt 244001
You may examine the AD docket on
the internet at https://
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–
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
26877
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 https://
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
ˆ
Agencia Nacional de Aviacao 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 https://
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
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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
Modification ............
Up to 270 work-hours × $85 per hour = $22,950 ..
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.
daltland on DSKBBV9HB2PROD with PROPOSALS
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
VerDate Sep<11>2014
17:25 Jun 08, 2018
Jkt 244001
Parts cost
$3,200
Cost per product
Up to $26,150 ................
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
PO 00000
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Fmt 4702
Sfmt 4702
Cost on U.S. operators
Up to $2,222,750.
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.
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Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules
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(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
VerDate Sep<11>2014
17:25 Jun 08, 2018
Jkt 244001
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.
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26879
(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
ˆ
Agencia Nacional de Aviacao 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
https://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 Sao
Jose dos Campos—SP—Brazil; telephone: +55
12 3927–5852 or +55 12 3309–0732; fax: +55
12 3927–7546; email:
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Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules
distrib@embraer.com.br; internet: https://
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.
Examining the AD Docket
[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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
https://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
daltland on DSKBBV9HB2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:25 Jun 08, 2018
Jkt 244001
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 https://
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 examine the AD docket on
the internet at https://
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 https://
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
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
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 https://
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.
E:\FR\FM\11JNP1.SGM
11JNP1
]]>Agencies
[Federal Register Volume 83, Number 112 (Monday, June 11, 2018)]
[Proposed Rules]
[Pages 26877-26880]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12228]
=======================================================================
-----------------------------------------------------------------------
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 https://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 S[atilde]o Jose dos Campos--SP--Brazil;
telephone: +55 12 3927-5852 or +55 12 3309-0732; fax: +55 12 3927-7546;
email: [email protected]; internet: https://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 https://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 https://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
Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]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 https://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
[[Page 26878]]
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
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Modification.................. Up to 270 work-hours $3,200 Up to $26,150....... Up to $2,222,750.
x $85 per hour =
$22,950.
----------------------------------------------------------------------------------------------------------------
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 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.
[[Page 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: [email protected]. 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 Ag[ecirc]ncia
Nacional de Avia[ccedil][atilde]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 https://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 S[atilde]o Jose dos
Campos--SP--Brazil; telephone: +55 12 3927-5852 or +55 12 3309-0732;
fax: +55 12 3927-7546; email:
[[Page 26880]]
[email protected]; internet: https://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
