Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters, 58638-58641 [2019-23832]
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Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by a report of
failure of a wing strut leak test due to a
missing bolt on the firewall. The FAA is
issuing this AD to address a hole in the
firewall, which could allow flammable fluid
leakage in the strut area. This leakage could
overwhelm the drainage provision, enter the
engine compartment, and result in an
uncontrollable engine fire and consequent
structural failure of the wing.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Leak Test and Corrective Action
Within 12 months after the effective date
of this AD: Do a one-time leak (functional)
test of the strut upper spar areas for the left
and right wing struts, by doing the actions
specified in paragraphs (g)(1) through (5) of
this AD. A review of airplane maintenance
records is acceptable in lieu of this test if it
can be conclusively determined from that
review that the leak test was previously
accomplished and successfully completed.
(1) Put a plug in the strut forward drain
outlet (this drain outlet is labeled as ‘‘pylon
strut’’). Put an empty container below the
strut forward drain outlet to collect water
drained through this outlet.
(2) Apply 381 to 387 fluid ounces (11.3 to
11.4 liters) of water in 2.5 to 3.5 minutes, to
the strut upper spar (strut areas between the
forward and mid-vapor barriers).
(3) Make sure that no leakage occurred
after doing the action specified in paragraph
(g)(2) of this AD.
(4) Remove the plug from the strut forward
drain outlet and make sure that the water is
drained through the strut forward drain
outlet only.
(5) After 3 minutes from accomplishing the
action specified in paragraph (g)(4) of this
AD, measure the water collected in the
container, and do the applicable actions
specified in paragraphs (g)(5)(i) through (iii)
of this AD.
(i) If leaks were found, do corrective action
before further flight using a method approved
in accordance with the procedures specified
in paragraph (h) of this AD.
(ii) If no leaks were found and less than
354 fluid ounces (10.5 liters) of water is
collected in the container, do corrective
action before further flight using a method
approved in accordance with the procedures
specified in paragraph (h) of this AD.
(ii) Before further flight after
accomplishing any corrective action required
by paragraph (g)(5)(i) or (ii) of this AD, repeat
the actions specified in paragraphs (g)(1)
through (5) of this AD until successful
completion of the test (i.e., no leaks are found
and 354 fluid ounces (10.5 liters) of water or
more is measured in the container).
Note 1 to paragraph (g): Additional
guidance for performing the leak (functional)
test can be found in Boeing Model 787
Aircraft Maintenance Manual (AMM), 54–
65–01, Strut Spar—Upper—Functional Test.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 the attention of
the person identified in paragraph (i)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(i) Related Information
(1) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3553;
email: takahisa.kobayashi@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. For information on
the availability of this material at the FAA,
call 206–231–3195.
Issued in Des Moines, Washington, on
October 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–23788 Filed 10–31–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0827; Product
Identifier 2019–SW–014–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
Helicopters
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Notice of proposed rulemaking
(NPRM).
ACTION:
The FAA proposes to
supersede Airworthiness Directive (AD)
2011–12–07 for Eurocopter France (now
Airbus Helicopters) Model SA–365C,
SA–365C1, SA–365C2, SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters. AD 2011–12–07
currently requires repetitively
inspecting the adhesive bead between
the bushings and the Starflex star
(Starflex) arms and the Starflex arm
ends. Since the FAA issued AD 2011–
12–07, Airbus Helicopters has
developed an improved Starflex. This
proposed AD would retain the
requirements of AD 2011–12–07 and
revise the Applicability paragraph by
omitting helicopters with the improved
Starflex installed. The FAA is proposing
this AD to address the unsafe condition
on these products.
DATES: The FAA must receive comments
on this proposed AD by December 31,
2019.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
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–2019–
0827; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the European Aviation Safety
Agency (EASA) AD, the economic
evaluation, any comments received and
other information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
For service information identified in
this proposed rule, contact Airbus
Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–
0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
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may view this service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Comments Invited
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views. The FAA also
invites comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
The FAA will file in the docket all
comments that the FAA receives, as
well as a report summarizing each
substantive public contact with FAA
personnel concerning this proposed
rulemaking. Before acting on this
proposal, the FAA will consider all
comments received on or before the
closing date for comments. The FAA
will consider comments filed after the
comment period has closed if it is
possible to do so without incurring
expense or delay. The FAA may change
this proposal in light of the comments
received.
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Discussion
The FAA issued AD 2011–12–07,
Amendment 39–16714 (76 FR 35346,
June 17, 2011) (‘‘AD 2011–12–07’’) for
Eurocopter France (now Airbus
Helicopters) Model SA–365C, SA–
365C1, SA–365C2, SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters. AD 2011–12–07
requires repetitively inspecting the
adhesive bead between the bushings
and the Starflex arms for a crack, a gap,
and loss of the adhesive bead,
inspecting the Starflex arm ends for
delamination, and replacing the Starflex
if any of these conditions are found. AD
2011–12–07 was prompted by three
cases of deterioration of a Starflex arm
end. In two of these cases, the
deterioration caused high amplitude
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vibrations in flight, compelling the pilot
to make a precautionary landing. The
requirements of AD 2011–12–07 are
intended to prevent failure of the
Starflex, high-amplitude vibrations in
flight, and subsequent loss of control of
the helicopter.
Actions Since AD 2011–12–07 Was
Issued
Since the FAA issued AD 2011–12–
07, Airbus Helicopters has developed
new part-numbered Starflex, 365A31–
1212–00 and 365A31–1213–00, with
different material. This change in
material improves the reliability and
technical performance of the Starflex,
improves temperature-related behavior
in the area of the Starflex arm ends, and
increases dimension margins.
Subsequently, Airbus Helicopters has
extended the inspection interval of
Starflex arm ends with these Starflex
installed. Airbus Helicopters identifies
helicopters with Starflex part number
365A31–1212–00 or 365A31–1213–00
installed as Modification (MOD)
0762C37.
Accordingly, EASA, which is the
Technical Agent for the Member States
of the European Union, issued AD No.
2008–0165R1, dated June 30, 2017
(EASA AD 2008–0165R1), to address
this unsafe condition for Airbus
Helicopters Model SA 365 N, SA 365
N1, AS 365 N2, AS 365 N3, SA 365 C,
SA 365 C1, SA 365 C2, SA 365 C3 and
SA 366 G1 helicopters, except
helicopters with MOD 0762C37
installed in production. EASA advises
that the Airbus Helicopters Starflex
manufactured with improved materials
make the 10-hour repetitive inspections
specified in the original issue of EASA
AD 2008–0165R1 unnecessary. EASA
AD 2008–0165R1 retains the repetitive
inspections from the original issue but
does not apply to helicopters with the
new Starflex.
Also since the FAA issued AD 2011–
12–07, Eurocopter France changed its
name to Airbus Helicopters. This
proposed AD reflects that change and
updates the contact information to
obtain service documentation.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in its AD. The FAA is proposing this AD
after evaluating all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other helicopters of the same
type designs.
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Related Service Information Under 1
CFR Part 51
The FAA reviewed one document that
co-publishes four Airbus Helicopters
Emergency Alert Service Bulletin
(EASB) identification numbers: No.
05.00.51 for Model 365N-series
helicopters, No. 05.35 for Model 366G1
helicopters, No. 05.28 for Model 365Cseries helicopters, and No. 05.00.21 for
non FAA-type certificated military
helicopters, all Revision 4 and dated
November 20, 2014. EASB Nos.
05.00.51, 05.35, and 05.28 are proposed
for incorporation by reference in this
proposed AD. EASB No. 05.00.21 is not
proposed for incorporation by reference
in this proposed AD.
This service information specifies
visually inspecting the adhesive bead on
the bushes of the Starflex arm ends for
bonding failure of the bushes and
distortion of the Starflex arm ends. This
service information also specifies
inspecting the leading edges and the
trailing edges of the Starflex arm ends
for delamination.
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.
Other Related Service Information
The FAA reviewed Airbus Helicopters
Master Servicing Manual (MSM) AS 365
N for Model SA–365N helicopters, MSM
AS 365 N1 for Model SA–365N1
helicopters, MSM AS 365 N2 for Model
AS–365N2 helicopters, and MSM AS
365 N3 for Model AS 365 N3
helicopters, all Revision 7 and dated
October 9, 2017. This service
information provides a schedule of
maintenance tasks for the helicopters.
The FAA also reviewed one document
that co-publishes four Eurocopter EASB
identification numbers: No. 05.00.51 for
Model 365N-series helicopters, No.
05.35 for Model 366G1 helicopters, No.
05.28 for Model 365C-series helicopters,
and No. 05.00.21 for non FAA-type
certificated military helicopters, all
Revision 3 and dated August 18, 2008.
This service information specifies the
same Accomplishment Instructions as
Revision 4, which is issued under the
name Airbus Helicopters, although
Revision 4 excludes helicopters that
have MOD 0762C37 installed.
Proposed AD Requirements
This proposed AD would retain the
requirements of AD 2011–12–07 to
repetitively inspect the adhesive bead
between the bushings and the Starflex
arms for a crack, a gap, and loss of the
adhesive bead, and repetitively inspect
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the Starflex arm ends for delamination.
However, this proposed AD would not
apply to helicopters with MOD 0762C37
installed.
Differences Between This Proposed AD
and the EASA AD
The EASA AD uses the word ‘‘check,’’
whereas this proposed AD uses the
word ‘‘inspect’’ instead. In some ADs,
the FAA uses the word ‘‘check’’ to
designate specific actions that may be
performed by the owner/operator (pilot).
An ‘‘inspection’’ is a maintenance
action that must be performed by a
certificated person as specified in 14
CFR 43.3.
Costs of Compliance
The FAA estimates that this proposed
AD affects 35 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this AD. Labor
costs are estimated at $85 per workhour.
Inspecting the Starflex would take
about 0.25 work-hour for an estimated
cost of $21 per helicopter and $735 for
the U.S. fleet per inspection cycle.
Replacing the Starflex would take about
10 work-hours and parts would cost
about $65,900 for an estimated cost of
$66,750.
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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.
The FAA is 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.
Regulatory Findings
The FAA 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
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responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) 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.
The FAA prepared an economic
evaluation of the estimated costs to
comply with this proposed AD and
placed it in the AD docket.
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
removing Airworthiness Directive (AD)
2011–12–07, Amendment 39–16714 (76
FR 35346, June 17, 2011), and adding
the following new AD:
■
Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France):
Docket No. FAA–2019–0827; Product
Identifier 2019–SW–014–AD.
(a) Applicability
This AD applies to Airbus Helicopters
(Type Certificate previously held by
Eurocopter France) Model SA–365C, SA–
365C1, SA–365C2, SA–365N, SA–365N1,
AS–365N2, AS 365 N3, and SA–366G1
helicopters, certificated in any category,
without Airbus Helicopters Modification
0762C37 (starflex arm part number (P/N)
365A31–1212–00 or P/N 365A31–1213–00)
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of the Starflex star (Starflex) arm. This
condition could result in high amplitude
vibrations in flight and subsequent loss of
control of the helicopter.
(c) Affected ADs
This AD replaces AD 2011–12–07,
Amendment 39–16714 (76 FR 35346, June
17, 2011).
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(d) Comments Due Date
The FAA must receive comments by
December 31, 2019.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
Within 10 hours time-in-service (TIS) and
thereafter at intervals not to exceed 10 hours
TIS:
(1) Visually inspect the adhesive bead
between the bushing and the Starflex arm for
a crack, a gap, and loss of the adhesive bead,
and inspect the Starflex arm ends for
delamination in accordance with the
Accomplishment Instructions, paragraphs
2.B.1. and 2.B.2. of Airbus Helicopters
Emergency Alert Service Bulletin (EASB) No.
05.00.51, Revision 4, dated November 20,
2014 (EASB 05.00.51), EASB No. 05.35,
Revision 4, dated November 20, 2014 (EASB
05.35), or EASB No. 05.28, Revision 4, dated
November 20, 2014 (EASB 05.28), as
applicable to your model helicopter.
(2) If there is a crack in the shockproof
paint around the entire adhesive bead where
the Starflex arm joins the bushing (as shown
in Figure 2 of EASB 05.00.51, EASB 05.35,
or EASB 05.28, as applicable to your model
helicopter), a gap between the adhesive bead
and the bushing (as shown in Figure 3 of
EASB 05.00.51, EASB 05.35, or EASB 05.28,
as applicable to your model helicopter),
delamination of a Starflex arm end (as shown
in Figure 4 of EASB 05.00.51, EASB 05.35,
or EASB 05.28, as applicable to your model
helicopter), or loss of adhesive bead (as
shown in Figure 5 of EASB 05.00.51, EASB
05.35, or EASB 05.28, as applicable to your
model helicopter), replace the Starflex before
further flight.
(g) Credit for Previous Actions
Actions accomplished before the effective
date of this AD in accordance with the
procedures specified in Eurocopter
Emergency Alert Service Bulletin Nos.
05.00.51, 05.35, or 05.28, all Revision 3 and
dated August 18, 2008, as applicable to your
model helicopter, are considered acceptable
for compliance with the corresponding
actions specified in paragraph (f) of this AD
as long as the last inspection was
accomplished within the prior 10 hours TIS.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
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certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters Master Servicing
Manual (MSM) AS 365 N, MSM AS 365 N1,
MSM AS 365 N2, and MSM AS 365 N3, all
Revision 7 and dated October 9, 2017; and
Eurocopter Emergency Alert Service Bulletin
Nos. 05.00.51, 05.35, 05.28, and 05.00.21, all
Revision 3 and dated August 18, 2008, which
are not incorporated by reference, contain
additional information about the subject of
this AD. For service information identified in
this AD, contact Airbus Helicopters, 2701 N
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.helicopters.airbus.com/website/en/ref/
Technical-Support_73.html. You may view a
copy of the service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2008–0165R1, dated June 30, 2017. You
may view the EASA AD on the internet at
https://www.regulations.gov in the AD Docket.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
Issued in Fort Worth, Texas, on October 21,
2019.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–23832 Filed 10–31–19; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R09–OAR–2018–0562; FRL–10001–
51–Region 9]
Clean Air Plans; 2008 8-Hour Ozone
Nonattainment Area Requirements;
Determination of Attainment by the
Attainment Date; Imperial County,
California
Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
AGENCY:
The Environmental Protection
Agency (EPA) is proposing to approve
two state implementation plan (SIP)
revisions submitted by the State of
California to meet Clean Air Act (CAA
or ‘‘Act’’) requirements for the 2008
ozone national ambient air quality
standards (NAAQS) in the Imperial
County nonattainment area, as follows.
The EPA proposes to approve the
‘‘Imperial County 2017 State
Implementation Plan for the 2008 8-
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SUMMARY:
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Hour Ozone Standard’’ (‘‘Imperial
Ozone Plan’’ or ‘‘Plan’’) and the portions
of the ‘‘2018 Updates to the California
State Implementation Plan’’ (‘‘2018 SIP
Update’’) that address the requirement
for a reasonable further progress (RFP)
demonstration for the Imperial County
for the 2008 ozone standards. In
addition, the EPA is proposing to
determine, based on a separate
demonstration submitted by the State of
California, that the Imperial County
nonattainment area would have attained
the 2008 ozone NAAQS by the
‘‘Moderate’’ area attainment date of July
20, 2018, but for emissions emanating
from outside of the United States, and
therefore would no longer be subject to
the CAA requirements pertaining to
reclassification upon failure to attain. If
we finalize these proposed actions, the
Imperial County nonattainment area
would remain classified as a Moderate
nonattainment area for the 2008 ozone
NAAQS.
DATES: Any comments must arrive by
December 2, 2019.
ADDRESSES: Submit your comments,
identified by Docket ID No. EPA–R09–
OAR–2018–0562, at https://
www.regulations.gov. For comments
submitted at Regulations.gov, follow the
online instructions for submitting
comments. Once submitted, comments
cannot be edited or removed from
Regulations.gov. The EPA may publish
any comment received to its public
docket. Do not submit electronically any
information you consider to be
Confidential Business Information (CBI)
or other information whose disclosure is
restricted by statute. Multimedia
submissions (audio, video, etc.) must be
accompanied by a written comment.
The written comment is considered the
official comment and should include
discussion of all points you wish to
make. The EPA will generally not
consider comments or comment
contents located outside of the primary
submission (i.e., on the web, cloud, or
other file sharing system). For
additional submission methods, please
contact the person identified in the FOR
FURTHER INFORMATION CONTACT section.
For the full EPA public comment policy,
information about CBI or multimedia
submissions, and general guidance on
making effective comments, please visit
https://www.epa.gov/dockets/
commenting-epa-dockets.
FOR FURTHER INFORMATION CONTACT: Rory
Mays, Air Planning Office (AIR–2), EPA
Region IX, (415) 972–3227, mays.rory@
epa.gov.
SUPPLEMENTARY INFORMATION:
Throughout this document, ‘‘we,’’ ‘‘us,’’
and ‘‘our’’ refer to the EPA. The EPA
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
58641
proposes to approve the portions of the
Imperial Ozone Plan that address the
requirements for emissions statements, a
base year emissions inventory, a
reasonably available control measures
(RACM) demonstration, a demonstration
of attainment of the standards by the
applicable attainment date but for
emissions emanating from outside of the
United States, and motor vehicle
emission budgets. The EPA proposes
that the requirements for contingency
measures for failing to meet RFP would
be moot if we finalize our proposed
determination that Imperial County has
met its 2017 RFP targets. The EPA also
proposes that contingency measures for
failing to attain the standards would not
be required if we finalize our proposed
approval of the State’s demonstrations
of attainment by the attainment date but
for international emissions. The EPA
proposes to approve the portions of the
2018 SIP Update that address the
requirement for a reasonable further
progress (RFP) demonstration for the
Imperial County for the 2008 ozone
standards.
Table of Contents
I. Background
A. Ozone Standards, Area Designations,
and SIPs
B. Imperial County Ozone Nonattainment
Area
II. Imperial Ozone Plan and 2018 SIP Update
A. Overarching Requirements
B. Requirements for International Border
Areas
C. Summary of the Imperial Ozone Plan
and 2018 SIP Update
D. Emissions Statement Certification
E. Emissions Inventories
F. Reasonably Available Control Measures
Demonstration
G. Demonstration of Attainment but for
International Emissions
H. Rate of Progress and Reasonable Further
Progress Demonstration
I. Motor Vehicle Emission Budgets
J. Contingency Measures
K. Other Requirements
III. Imperial County Ozone Determination of
Attainment but for International
Emissions
A. Statutory and Regulatory Requirements
B. Summary of State’s Submission
C. EPA Review of State’s Submission
IV. Proposed Action
V. Statutory and Executive Order Reviews
I. Background
A. Ozone Standards, Area Designations,
and SIPs
Ground-level ozone pollution is
formed from the reaction of volatile
organic compounds (VOC) and oxides of
nitrogen (NOX) in the presence of
sunlight. These two pollutants, referred
to as ozone precursors, are emitted by
many types of sources, including on-
E:\FR\FM\01NOP1.SGM
01NOP1
]]>Agencies
[Federal Register Volume 84, Number 212 (Friday, November 1, 2019)]
[Proposed Rules]
[Pages 58638-58641]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23832]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2011-12-07 for Eurocopter France (now Airbus Helicopters) Model SA-
365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and
SA-366G1 helicopters. AD 2011-12-07 currently requires repetitively
inspecting the adhesive bead between the bushings and the Starflex star
(Starflex) arms and the Starflex arm ends. Since the FAA issued AD
2011-12-07, Airbus Helicopters has developed an improved Starflex. This
proposed AD would retain the requirements of AD 2011-12-07 and revise
the Applicability paragraph by omitting helicopters with the improved
Starflex installed. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by December
31, 2019.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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-2019-
0827; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this proposed AD, the European Aviation Safety Agency (EASA) AD, the
economic evaluation, any comments received and other information. The
street address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You
[[Page 58639]]
may view this service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.
The FAA will file in the docket all comments that the FAA receives,
as well as a report summarizing each substantive public contact with
FAA personnel concerning this proposed rulemaking. Before acting on
this proposal, the FAA will consider all comments received on or before
the closing date for comments. The FAA will consider comments filed
after the comment period has closed if it is possible to do so without
incurring expense or delay. The FAA may change this proposal in light
of the comments received.
Discussion
The FAA issued AD 2011-12-07, Amendment 39-16714 (76 FR 35346, June
17, 2011) (``AD 2011-12-07'') for Eurocopter France (now Airbus
Helicopters) Model SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters. AD 2011-12-07 requires
repetitively inspecting the adhesive bead between the bushings and the
Starflex arms for a crack, a gap, and loss of the adhesive bead,
inspecting the Starflex arm ends for delamination, and replacing the
Starflex if any of these conditions are found. AD 2011-12-07 was
prompted by three cases of deterioration of a Starflex arm end. In two
of these cases, the deterioration caused high amplitude vibrations in
flight, compelling the pilot to make a precautionary landing. The
requirements of AD 2011-12-07 are intended to prevent failure of the
Starflex, high-amplitude vibrations in flight, and subsequent loss of
control of the helicopter.
Actions Since AD 2011-12-07 Was Issued
Since the FAA issued AD 2011-12-07, Airbus Helicopters has
developed new part-numbered Starflex, 365A31-1212-00 and 365A31-1213-
00, with different material. This change in material improves the
reliability and technical performance of the Starflex, improves
temperature-related behavior in the area of the Starflex arm ends, and
increases dimension margins. Subsequently, Airbus Helicopters has
extended the inspection interval of Starflex arm ends with these
Starflex installed. Airbus Helicopters identifies helicopters with
Starflex part number 365A31-1212-00 or 365A31-1213-00 installed as
Modification (MOD) 0762C37.
Accordingly, EASA, which is the Technical Agent for the Member
States of the European Union, issued AD No. 2008-0165R1, dated June 30,
2017 (EASA AD 2008-0165R1), to address this unsafe condition for Airbus
Helicopters Model SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 365 C,
SA 365 C1, SA 365 C2, SA 365 C3 and SA 366 G1 helicopters, except
helicopters with MOD 0762C37 installed in production. EASA advises that
the Airbus Helicopters Starflex manufactured with improved materials
make the 10-hour repetitive inspections specified in the original issue
of EASA AD 2008-0165R1 unnecessary. EASA AD 2008-0165R1 retains the
repetitive inspections from the original issue but does not apply to
helicopters with the new Starflex.
Also since the FAA issued AD 2011-12-07, Eurocopter France changed
its name to Airbus Helicopters. This proposed AD reflects that change
and updates the contact information to obtain service documentation.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determined that an
unsafe condition is likely to exist or develop on other helicopters of
the same type designs.
Related Service Information Under 1 CFR Part 51
The FAA reviewed one document that co-publishes four Airbus
Helicopters Emergency Alert Service Bulletin (EASB) identification
numbers: No. 05.00.51 for Model 365N-series helicopters, No. 05.35 for
Model 366G1 helicopters, No. 05.28 for Model 365C-series helicopters,
and No. 05.00.21 for non FAA-type certificated military helicopters,
all Revision 4 and dated November 20, 2014. EASB Nos. 05.00.51, 05.35,
and 05.28 are proposed for incorporation by reference in this proposed
AD. EASB No. 05.00.21 is not proposed for incorporation by reference in
this proposed AD.
This service information specifies visually inspecting the adhesive
bead on the bushes of the Starflex arm ends for bonding failure of the
bushes and distortion of the Starflex arm ends. This service
information also specifies inspecting the leading edges and the
trailing edges of the Starflex arm ends for delamination.
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.
Other Related Service Information
The FAA reviewed Airbus Helicopters Master Servicing Manual (MSM)
AS 365 N for Model SA-365N helicopters, MSM AS 365 N1 for Model SA-
365N1 helicopters, MSM AS 365 N2 for Model AS-365N2 helicopters, and
MSM AS 365 N3 for Model AS 365 N3 helicopters, all Revision 7 and dated
October 9, 2017. This service information provides a schedule of
maintenance tasks for the helicopters.
The FAA also reviewed one document that co-publishes four
Eurocopter EASB identification numbers: No. 05.00.51 for Model 365N-
series helicopters, No. 05.35 for Model 366G1 helicopters, No. 05.28
for Model 365C-series helicopters, and No. 05.00.21 for non FAA-type
certificated military helicopters, all Revision 3 and dated August 18,
2008. This service information specifies the same Accomplishment
Instructions as Revision 4, which is issued under the name Airbus
Helicopters, although Revision 4 excludes helicopters that have MOD
0762C37 installed.
Proposed AD Requirements
This proposed AD would retain the requirements of AD 2011-12-07 to
repetitively inspect the adhesive bead between the bushings and the
Starflex arms for a crack, a gap, and loss of the adhesive bead, and
repetitively inspect
[[Page 58640]]
the Starflex arm ends for delamination. However, this proposed AD would
not apply to helicopters with MOD 0762C37 installed.
Differences Between This Proposed AD and the EASA AD
The EASA AD uses the word ``check,'' whereas this proposed AD uses
the word ``inspect'' instead. In some ADs, the FAA uses the word
``check'' to designate specific actions that may be performed by the
owner/operator (pilot). An ``inspection'' is a maintenance action that
must be performed by a certificated person as specified in 14 CFR 43.3.
Costs of Compliance
The FAA estimates that this proposed AD affects 35 helicopters of
U.S. Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Inspecting the Starflex would take about 0.25 work-hour for an
estimated cost of $21 per helicopter and $735 for the U.S. fleet per
inspection cycle. Replacing the Starflex would take about 10 work-hours
and parts would cost about $65,900 for an estimated cost of $66,750.
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.
The FAA is 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.
Regulatory Findings
The FAA 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, I certify this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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.
The FAA prepared an economic evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 removing Airworthiness Directive (AD)
2011-12-07, Amendment 39-16714 (76 FR 35346, June 17, 2011), and adding
the following new AD:
Airbus Helicopters (Type Certificate Previously Held by Eurocopter
France): Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-
AD.
(a) Applicability
This AD applies to Airbus Helicopters (Type Certificate
previously held by Eurocopter France) Model SA-365C, SA-365C1, SA-
365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters, certificated in any category, without Airbus
Helicopters Modification 0762C37 (starflex arm part number (P/N)
365A31-1212-00 or P/N 365A31-1213-00) installed.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of the Starflex
star (Starflex) arm. This condition could result in high amplitude
vibrations in flight and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD replaces AD 2011-12-07, Amendment 39-16714 (76 FR 35346,
June 17, 2011).
(d) Comments Due Date
The FAA must receive comments by December 31, 2019.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
Within 10 hours time-in-service (TIS) and thereafter at
intervals not to exceed 10 hours TIS:
(1) Visually inspect the adhesive bead between the bushing and
the Starflex arm for a crack, a gap, and loss of the adhesive bead,
and inspect the Starflex arm ends for delamination in accordance
with the Accomplishment Instructions, paragraphs 2.B.1. and 2.B.2.
of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No.
05.00.51, Revision 4, dated November 20, 2014 (EASB 05.00.51), EASB
No. 05.35, Revision 4, dated November 20, 2014 (EASB 05.35), or EASB
No. 05.28, Revision 4, dated November 20, 2014 (EASB 05.28), as
applicable to your model helicopter.
(2) If there is a crack in the shockproof paint around the
entire adhesive bead where the Starflex arm joins the bushing (as
shown in Figure 2 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as
applicable to your model helicopter), a gap between the adhesive
bead and the bushing (as shown in Figure 3 of EASB 05.00.51, EASB
05.35, or EASB 05.28, as applicable to your model helicopter),
delamination of a Starflex arm end (as shown in Figure 4 of EASB
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model
helicopter), or loss of adhesive bead (as shown in Figure 5 of EASB
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model
helicopter), replace the Starflex before further flight.
(g) Credit for Previous Actions
Actions accomplished before the effective date of this AD in
accordance with the procedures specified in Eurocopter Emergency
Alert Service Bulletin Nos. 05.00.51, 05.35, or 05.28, all Revision
3 and dated August 18, 2008, as applicable to your model helicopter,
are considered acceptable for compliance with the corresponding
actions specified in paragraph (f) of this AD as long as the last
inspection was accomplished within the prior 10 hours TIS.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or
[[Page 58641]]
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters Master Servicing Manual (MSM) AS 365 N,
MSM AS 365 N1, MSM AS 365 N2, and MSM AS 365 N3, all Revision 7 and
dated October 9, 2017; and Eurocopter Emergency Alert Service
Bulletin Nos. 05.00.51, 05.35, 05.28, and 05.00.21, all Revision 3
and dated August 18, 2008, which are not incorporated by reference,
contain additional information about the subject of this AD. For
service information identified in this AD, contact Airbus
Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
You may view a copy of the service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2008-0165R1, dated June 30, 2017. You
may view the EASA AD on the internet at https://www.regulations.gov
in the AD Docket.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
Issued in Fort Worth, Texas, on October 21, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-23832 Filed 10-31-19; 8:45 am]
BILLING CODE 4910-13-P
