Airworthiness Directives; Airbus Helicopters, 39506-39509 [2017-17084]
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39506
Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
that a violation of Loan Program
Requirements constitutes default under
their respective agreements with SBA.
(1) Additional agreements by CDCs.
By obtaining approval for 504 loans
after October 20, 2017, a CDC consents
to the remedies in § 120.1500(e)(3) and
waives in advance any right it may have
to contest the validity of the
appointment of a receiver. The CDC
agrees that its consent to SBA’s
application to a Federal court of
competent jurisdiction for appointment
of a receiver of SBA’s choosing, an
injunction or other equitable relief, and
the CDC’s consent in advance to the
court’s granting of SBA’s application,
may be enforced upon any basis in law
or equity recognized by the court.
(2) Additional agreements by SBA
Supervised Lenders (except Other
Regulated SBLCs). By making SBA 7(a)
guaranteed loans after October 20, 2017,
an SBA Supervised Lender (except an
Other Regulated SBLC) consents to the
remedies in § 120.1500(c)(3) and waives
in advance any right it may have to
contest the validity of the appointment
of a receiver. The SBA Supervised
Lender agrees that its consent to SBA’s
application to a Federal court of
competent jurisdiction for appointment
of a receiver of SBA’s choosing, an
injunction or other equitable relief, and
the SBA Supervised Lender’s consent in
advance to the court’s granting of SBA’s
application, may be enforced upon any
basis in law or equity recognized by the
court.
*
*
*
*
*
■ 47. Amend § 120.1500 by revising
paragraph (c)(3) and adding paragraph
(e)(3) to read as follows:
§ 120.1500 Types of enforcement
actions—SBA Lenders.
sradovich on DSK3GMQ082PROD with RULES
*
*
*
*
*
(c) * * *
(3) Initiate request for appointment of
receiver and/or other relief. The SBA
may make application to any Federal
court of competent jurisdiction for the
court to take exclusive jurisdiction,
without notice, of an SBA Supervised
Lender, and SBA shall be entitled to the
appointment of a receiver of SBA’s
choosing to hold, administer, operate,
and/or liquidate the SBA Supervised
Lender; and to such injunctive or other
equitable relief as may be appropriate.
Without limiting the foregoing and with
SBA’s written consent, the receiver may
take possession of the portfolio of 7(a)
loans and sell such loans to a third
party, and/or take possession of
servicing activities of 7(a) loans and sell
such servicing rights to a third party.
*
*
*
*
*
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16:12 Aug 18, 2017
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(e) * * *
(3) Apply to any Federal court of
competent jurisdiction for the court to
take exclusive jurisdiction, without
notice, of the CDC, and SBA shall be
entitled to the appointment of a receiver
of SBA’s choosing to hold, administer,
operate and/or liquidate the CDC; and to
such injunctive or other equitable relief
as may be appropriate. Without limiting
the foregoing and with SBA’s consent,
the receiver may take possession of the
portfolio of 504 loans and/or pending
504 loan applications, including for the
purpose of carrying out an enforcement
order under paragraph (e)(1) of this
section.
■ 48. Amend § 120.1600 by:
■ a. Revising paragraph (a) introductory
text;
■ b. Adding paragraph (a)(6); and
■ c. Revising paragraph (b)(4).
The revisions and addition read as
follows:
§ 120.1600 General procedures for
enforcement actions against SBA Lenders,
SBA Supervised Lenders, Other Regulated
SBLCs, Management Officials, Other
Persons, Intermediaries, and NTAPs.
(a) In general. Except as otherwise set
forth for the enforcement actions listed
in paragraphs (a)(6), (b) and (c) of this
section, SBA will follow the procedures
listed below.
*
*
*
*
*
(6) Receiverships of Certified
Development Companies and/or other
relief. If SBA undertakes the
appointment of a receiver for a Certified
Development Company and/or
injunctive or other equitable relief,
paragraphs (a)(1) through (5) of this
section will not apply and SBA will
follow the applicable procedures under
Federal law to obtain such remedies and
to enforce the Certified Development
Company’s consent and waiver in
advance to those remedies.
(b) * * *
(4) Receiverships, transfer of assets
and servicing activities. If SBA
undertakes the appointment of a
receiver for, or the transfer of assets or
servicing rights of an SBA Supervised
Lender and/or injunctive or other
equitable relief, SBA will follow the
applicable procedures under Federal
law to obtain such remedies and to
enforce the SBA Supervised Lender’s
consent and waiver in advance to those
remedies.
*
*
*
*
*
■ 49. Amend § 120.1703 by revising
paragraph (a)(4) to read as follows:
§ 120.1703 Qualifications to be a Pool
Originator.
(a) * * *
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(4) Is in good standing with SBA (as
the SBA determines), and is Satisfactory
with the Office of the Comptroller of the
Currency (OCC) if it is a national bank,
the Federal Deposit Insurance
Corporation if it is a bank not regulated
by the OCC, the Financial Institutions
Regulatory Authority if it is a member,
the National Credit Union
Administration if it is a credit union, as
determined by SBA; and
*
*
*
*
*
■ 50. Amend § 120.1707 by revising the
fifth sentence and adding a sixth
sentence to read as follows:
§ 120.1707
Seller’s retained Loan Interest.
* * * In addition, in order to
complete such sale, Seller must have the
purchaser of its rights to the Pool Loan
execute an allonge to the Seller’s First
Lien Position 504 Loan Pool Guarantee
Agreement in a form acceptable to SBA,
acknowledging and accepting all terms
of the Seller’s First Lien Position 504
Loan Pool Guarantee Agreement, and
deliver the executed original allonge
and a copy of the corresponding First
Lien Position 504 Loan Pool Guarantee
Agreement to the CSA. All Pool Loan
payments related to a Seller Receipt and
Servicing Retention Amount proposed
for sale will be withheld by the CSA
pending SBA acknowledgement of
receipt of all executed documents
required to complete the transfer.
Subpart K—[Removed]
51. Remove Subpart K, consisting of
§§ 120.1800 through 120.1900.
■
Dated: August 11, 2017.
Linda E. McMahon,
Administrator.
[FR Doc. 2017–17447 Filed 8–18–17; 8:45 am]
BILLING CODE 8025–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0419; Product
Identifier 2015–SW–077–AD; Amendment
39–18991; AD 2017–17–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters (Airbus) Model AS332L2
SUMMARY:
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
sradovich on DSK3GMQ082PROD with RULES
and EC225LP helicopters. This AD
requires inspections of the main rotor
(M/R) blade attachment pins
(attachment pins). This AD was
prompted by a report of three cracked
attachment pins. The actions of this AD
are intended to detect and prevent an
unsafe condition on these products.
DATES: This AD is effective September
25, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of September 25, 2017.
ADDRESSES: For service information
identified in this final 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
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0419.
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–2017–
0419; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the European Aviation
Safety Agency (EASA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5116; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 11, 2017, at 82 FR 21956, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
VerDate Sep<11>2014
16:12 Aug 18, 2017
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Airbus Model AS332L2 helicopters with
an attachment pin part number (P/N)
332A31–2123–00 or P/N 332A31–2115–
20 installed and Model EC225LP
helicopters with an attachment pin P/N
332A31–3204–20 installed. The NPRM
proposed to require an initial and
recurring inspection of each attachment
pin for corrosion, a crack, and any
pitting. If there is a crack or any pitting,
the NPRM proposed to require replacing
the attachment pin. If there is corrosion,
the NPRM proposed to require removing
the corrosion up to a maximum of four
times. The NPRM also proposed to
require performing these inspections
prior to installing an attachment pin.
The proposed requirements were
intended to detect corrosion or a crack
in an attachment pin and prevent loss
of an M/R blade and subsequent loss of
control of the helicopter.
The NPRM was prompted by AD No.
2015–0016, dated January 30, 2015,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Airbus Model AS 332 L2
and EC 225 LP helicopters with certain
part-numbered attachment pins
installed. EASA advises of three cracked
attachment pins on a Model AS 332 L2
helicopter, which resulted from a
combination of factors including
corrosion that had initiated in the inner
diameter area of the attachment pin
chamfer. EASA states that if this
condition is not detected and corrected,
it may lead to failure of the attachment
pin with loss of control of the
helicopter. Due to design similarity,
Model EC225LP helicopters are also
affected by this issue.
For these reasons, EASA AD No.
2015–0016 requires repetitive
inspections of the attachment pins for
corrosion.
39507
and the public interest require adopting
the AD requirements as proposed.
Differences Between This AD and the
EASA AD
The EASA AD does not require an
inspection of the protective coating of
each attachment pin for Model EC225LP
helicopters. This AD requires inspecting
the protective coating of each
attachment pin for both model
helicopters. The EASA AD requires
ensuring there are no corrosion pits
without a corresponding corrective
action. This AD requires replacing an
attachment pin that has any pitting. The
EASA AD requires a non-destructive
inspection if in doubt about whether
there is a crack, while this AD does not.
Lastly, the EASA AD requires contacting
and returning to Airbus Helicopters any
attachment pin with a crack, and this
AD does not.
FAA’s Determination
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Helicopters Alert
Service Bulletin (ASB) No. AS332–
05.00.99, Revision 0, dated December
22, 2014 (AS332–05.00.99), for Model
AS332L2 helicopters and Airbus
Helicopters ASB No. EC225–05A040,
Revision 0, dated December 22, 2014
(EC225–05A040), for Model EC225LP
helicopters. Airbus Helicopters advises
of cracks discovered in attachment pins
that resulted from a combination of
factors, but mainly corrosion which
initiated in the inner diameter at the
chamfer. This service information
specifies repetitively inspecting for
corrosion and cracks and ensuring there
are no corrosion pits in the attachment
pins. If there is corrosion, this service
information allows an attachment pin to
be reworked up to four times before
removing it from service. If there is a
crack, this service information specifies
contacting and sending the attachment
pin to Airbus Helicopters.
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.
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are issuing this AD because we
evaluated all information provided by
EASA and determined the unsafe
condition exists and is likely to exist or
develop on other helicopters of these
same type designs and that air safety
Costs of Compliance
We estimate that this AD affects 5
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
Labor costs are estimated at $85 per
work-hour.
For Model AS332L2 helicopters, there
are no costs of compliance with this AD
because there are no helicopters with
this type certificate on the U.S. Registry.
For Model EC225LP helicopters,
which have ten attachment pins
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM.
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
installed, inspecting the attachment
pins takes about 1 work-hour for a total
cost of $85 per helicopter and $425 for
the U.S. fleet. Removing corrosion takes
about 1 work-hour for a total cost of $85
per attachment pin. Replacing an
attachment pin takes negligible
additional labor time and required parts
would cost about $5,720.
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
helicopters identified in this rulemaking
action.
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Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this 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.
16:12 Aug 18, 2017
Jkt 241001
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority for This Rulemaking
VerDate Sep<11>2014
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 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):
■
2017–17–01 Airbus Helicopters:
Amendment 39–18991; Docket No.
FAA–2017–0419; Product Identifier
2015–SW–077–AD.
(a) Applicability
This AD applies to the following
helicopters, certificated in any category:
(1) Model AS332L2 helicopters with a
main rotor (M/R) blade attachment pin
(attachment pin) part number (P/N) 332A31–
2123–00 or P/N 332A31–2115–20 installed;
and
(2) Model EC225LP helicopters with an
attachment pin P/N 332A31–3204–20
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
corrosion or a crack in an attachment pin.
This condition could result in loss of an M/
R blade and subsequent loss of control of the
helicopter.
(c) Effective Date
This AD becomes effective September 25,
2017.
(d) 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.
(e) Required Actions
(1) For Model AS332L2 helicopters, within
410 hours time-in-service (TIS), and for
Model EC225LP helicopters within 660 hours
TIS, remove each attachment pin and inspect
the protective coating on the inside of the
attachment pin for scratches and missing
protective coating.
(i) If there is a scratch or any missing
protective coating, sand the attachment pin
to remove the varnish in the area depicted as
‘‘Area A’’ in Figure 1 of Airbus Helicopters
Alert Service Bulletin (ASB) No. AS332–
05.00.99, Revision 0, dated December 22,
2014 (AS332–05.00.99), or Airbus
Helicopters ASB No. EC225–05A040,
Revision 0, dated December 22, 2014
(EC225–05A040), as applicable to your model
helicopter.
(ii) Using a 10X or higher power
magnifying glass, inspect for corrosion and
pitting at the chamfer. An example of pitting
is shown in the Accomplishment
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Instructions, paragraph 3.B.3., Note 1, of
AS332–05.00.99, and paragraph 3.B.2., Note
1, of EC225–05A040. If there is any
corrosion, remove the corrosion. If there is
any pitting, replace the attachment pin. Do
not sand the attachment pin to remove a
corrosion pit.
(iii) Using a 10X or higher power
magnifying glass, inspect the inside and
outside of the attachment pin for a crack in
the areas depicted as ‘‘Area A’’ and ‘‘Area B’’
in Figure 1 of AS332–05.00.99 or EC225–
05A040, as applicable to your model
helicopter. Pay particular attention to the
chamfer in ‘‘Area A.’’ If there is a crack,
remove the attachment pin from service.
(2) Thereafter, for Model AS332L2
helicopters, at intervals not to exceed 825
hours TIS or 26 months, whichever occurs
first; and for Model EC225LP helicopters, at
intervals not to exceed 1,320 hours TIS or 26
months, whichever occurs first; perform the
actions specified in paragraph (e)(1) of this
AD. Corrosion may be removed from an
attachment pin as specified in paragraph
(e)(1)(ii) of this AD a maximum of four times.
If there is a fifth occurrence of corrosion on
an attachment pin, before further flight,
remove the attachment pin from service.
(3) Do not install an attachment pin P/N
332A31–2123–00, P/N 332A31–2115–20, or
P/N 332A31–3204–20 on any helicopter
unless you have complied with the actions in
paragraph (e)(1) of this AD.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, FAA, may approve AMOCs for this
AD. Send your proposal to: David Hatfield,
Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5116; email 9–
ASW–FTW–AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
No. 2015–0016, dated January 30, 2015. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2017–0419.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
(i) Airbus Helicopters Alert Service
Bulletin (ASB) No. AS332–05.00.99, Revision
0, dated December 22, 2014.
(ii) Airbus Helicopters ASB No. EC225–
05A040, Revision 0, dated December 22,
2014.
(3) For Airbus Helicopters 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.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on August 7,
2017.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2017–17084 Filed 8–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0335; Product
Identifier 2017–NM–025–AD; Amendment
39–18994; AD 2017–17–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by a
report of cracks in the upper aft skin of
the right wing at certain fastener holes
along the rear spar upper chord. This
AD requires repetitive inspections for
cracking of the upper aft skin of the
wings, and repair if necessary. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective September
25, 2017.
The Director of the Federal Register
approved the incorporation by reference
sradovich on DSK3GMQ082PROD with RULES
16:12 Aug 18, 2017
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–2017–
0335; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Payman Soltani, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5313; fax: 562–627–
5210; email: payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
SUMMARY:
VerDate Sep<11>2014
of a certain publication listed in this AD
as of September 25, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0335.
Jkt 241001
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. The NPRM published in the
Federal Register on May 17, 2017 (82
FR 22619) (‘‘the NPRM’’). The NPRM
was prompted by a report of cracks in
the upper aft skin of the right wing at
certain fastener holes along the rear spar
upper chord. The NPRM proposed to
require repetitive inspections for
cracking of the upper aft skin of the
wings, and repair if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. The
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39509
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
Boeing and Robert Simpson
concurred with the content of the
NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the supplemental type
certificate (STC) ST01219SE does not
affect compliance with the actions
specified in the NPRM.
We agree with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) and
added paragraph (c)(2) to this AD to
state that installation of STC ST01219SE
does not affect the ability to accomplish
the actions required by this AD.
Therefore, for airplanes on which STC
ST01219SE is installed, a ‘‘change in
product’’ alternative method of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of 14 CFR 39.17.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–57A1332, dated January 3,
2017. This service information describes
procedures for repetitive detailed
inspections of the upper aft skin of the
wings for cracking. 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.
Costs of Compliance
We estimate that this AD affects 471
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
E:\FR\FM\21AUR1.SGM
21AUR1
]]>Agencies
[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39506-39509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17084]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0419; Product Identifier 2015-SW-077-AD; Amendment
39-18991; AD 2017-17-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters (Airbus) Model AS332L2
[[Page 39507]]
and EC225LP helicopters. This AD requires inspections of the main rotor
(M/R) blade attachment pins (attachment pins). This AD was prompted by
a report of three cracked attachment pins. The actions of this AD are
intended to detect and prevent an unsafe condition on these products.
DATES: This AD is effective September 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of September 25,
2017.
ADDRESSES: For service information identified in this final 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 may review the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is also available
on the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0419.
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-2017-
0419; or in person at the Docket Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the European Aviation Safety Agency (EASA) AD, any
incorporated-by-reference service information, the economic evaluation,
any comments received, and other information. The street address for
the Docket Operations Office (phone: 800-647-5527) is U.S. Department
of Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116;
email david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 11, 2017, at 82 FR 21956, the Federal Register published our
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR
part 39 by adding an AD that would apply to Airbus Model AS332L2
helicopters with an attachment pin part number (P/N) 332A31-2123-00 or
P/N 332A31-2115-20 installed and Model EC225LP helicopters with an
attachment pin P/N 332A31-3204-20 installed. The NPRM proposed to
require an initial and recurring inspection of each attachment pin for
corrosion, a crack, and any pitting. If there is a crack or any
pitting, the NPRM proposed to require replacing the attachment pin. If
there is corrosion, the NPRM proposed to require removing the corrosion
up to a maximum of four times. The NPRM also proposed to require
performing these inspections prior to installing an attachment pin. The
proposed requirements were intended to detect corrosion or a crack in
an attachment pin and prevent loss of an M/R blade and subsequent loss
of control of the helicopter.
The NPRM was prompted by AD No. 2015-0016, dated January 30, 2015,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus Model AS
332 L2 and EC 225 LP helicopters with certain part-numbered attachment
pins installed. EASA advises of three cracked attachment pins on a
Model AS 332 L2 helicopter, which resulted from a combination of
factors including corrosion that had initiated in the inner diameter
area of the attachment pin chamfer. EASA states that if this condition
is not detected and corrected, it may lead to failure of the attachment
pin with loss of control of the helicopter. Due to design similarity,
Model EC225LP helicopters are also affected by this issue.
For these reasons, EASA AD No. 2015-0016 requires repetitive
inspections of the attachment pins for corrosion.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are issuing this AD because we evaluated all information
provided by EASA and determined the unsafe condition exists and is
likely to exist or develop on other helicopters of these same type
designs and that air safety and the public interest require adopting
the AD requirements as proposed.
Differences Between This AD and the EASA AD
The EASA AD does not require an inspection of the protective
coating of each attachment pin for Model EC225LP helicopters. This AD
requires inspecting the protective coating of each attachment pin for
both model helicopters. The EASA AD requires ensuring there are no
corrosion pits without a corresponding corrective action. This AD
requires replacing an attachment pin that has any pitting. The EASA AD
requires a non-destructive inspection if in doubt about whether there
is a crack, while this AD does not. Lastly, the EASA AD requires
contacting and returning to Airbus Helicopters any attachment pin with
a crack, and this AD does not.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No.
AS332-05.00.99, Revision 0, dated December 22, 2014 (AS332-05.00.99),
for Model AS332L2 helicopters and Airbus Helicopters ASB No. EC225-
05A040, Revision 0, dated December 22, 2014 (EC225-05A040), for Model
EC225LP helicopters. Airbus Helicopters advises of cracks discovered in
attachment pins that resulted from a combination of factors, but mainly
corrosion which initiated in the inner diameter at the chamfer. This
service information specifies repetitively inspecting for corrosion and
cracks and ensuring there are no corrosion pits in the attachment pins.
If there is corrosion, this service information allows an attachment
pin to be reworked up to four times before removing it from service. If
there is a crack, this service information specifies contacting and
sending the attachment pin to Airbus Helicopters.
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.
Costs of Compliance
We estimate that this AD affects 5 helicopters of U.S. Registry. We
estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work-hour.
For Model AS332L2 helicopters, there are no costs of compliance
with this AD because there are no helicopters with this type
certificate on the U.S. Registry.
For Model EC225LP helicopters, which have ten attachment pins
[[Page 39508]]
installed, inspecting the attachment pins takes about 1 work-hour for a
total cost of $85 per helicopter and $425 for the U.S. fleet. Removing
corrosion takes about 1 work-hour for a total cost of $85 per
attachment pin. Replacing an attachment pin takes negligible additional
labor time and required parts would cost about $5,720.
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 helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2017-17-01 Airbus Helicopters: Amendment 39-18991; Docket No. FAA-
2017-0419; Product Identifier 2015-SW-077-AD.
(a) Applicability
This AD applies to the following helicopters, certificated in
any category:
(1) Model AS332L2 helicopters with a main rotor (M/R) blade
attachment pin (attachment pin) part number (P/N) 332A31-2123-00 or
P/N 332A31-2115-20 installed; and
(2) Model EC225LP helicopters with an attachment pin P/N 332A31-
3204-20 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as corrosion or a crack in
an attachment pin. This condition could result in loss of an M/R
blade and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective September 25, 2017.
(d) 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.
(e) Required Actions
(1) For Model AS332L2 helicopters, within 410 hours time-in-
service (TIS), and for Model EC225LP helicopters within 660 hours
TIS, remove each attachment pin and inspect the protective coating
on the inside of the attachment pin for scratches and missing
protective coating.
(i) If there is a scratch or any missing protective coating,
sand the attachment pin to remove the varnish in the area depicted
as ``Area A'' in Figure 1 of Airbus Helicopters Alert Service
Bulletin (ASB) No. AS332-05.00.99, Revision 0, dated December 22,
2014 (AS332-05.00.99), or Airbus Helicopters ASB No. EC225-05A040,
Revision 0, dated December 22, 2014 (EC225-05A040), as applicable to
your model helicopter.
(ii) Using a 10X or higher power magnifying glass, inspect for
corrosion and pitting at the chamfer. An example of pitting is shown
in the Accomplishment Instructions, paragraph 3.B.3., Note 1, of
AS332-05.00.99, and paragraph 3.B.2., Note 1, of EC225-05A040. If
there is any corrosion, remove the corrosion. If there is any
pitting, replace the attachment pin. Do not sand the attachment pin
to remove a corrosion pit.
(iii) Using a 10X or higher power magnifying glass, inspect the
inside and outside of the attachment pin for a crack in the areas
depicted as ``Area A'' and ``Area B'' in Figure 1 of AS332-05.00.99
or EC225-05A040, as applicable to your model helicopter. Pay
particular attention to the chamfer in ``Area A.'' If there is a
crack, remove the attachment pin from service.
(2) Thereafter, for Model AS332L2 helicopters, at intervals not
to exceed 825 hours TIS or 26 months, whichever occurs first; and
for Model EC225LP helicopters, at intervals not to exceed 1,320
hours TIS or 26 months, whichever occurs first; perform the actions
specified in paragraph (e)(1) of this AD. Corrosion may be removed
from an attachment pin as specified in paragraph (e)(1)(ii) of this
AD a maximum of four times. If there is a fifth occurrence of
corrosion on an attachment pin, before further flight, remove the
attachment pin from service.
(3) Do not install an attachment pin P/N 332A31-2123-00, P/N
332A31-2115-20, or P/N 332A31-3204-20 on any helicopter unless you
have complied with the actions in paragraph (e)(1) of this AD.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, FAA, may approve
AMOCs for this AD. Send your proposal to: David Hatfield, Aviation
Safety Engineer, Safety Management Section, Rotorcraft Standards
Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone
(817) 222-5116; email 9-ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) No. 2015-0016, dated January 30, 2015. You may view
the EASA AD on the Internet at https://www.regulations.gov in Docket
No. FAA-2017-0419.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
[[Page 39509]]
(i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-
05.00.99, Revision 0, dated December 22, 2014.
(ii) Airbus Helicopters ASB No. EC225-05A040, Revision 0, dated
December 22, 2014.
(3) For Airbus Helicopters 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.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 7, 2017.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2017-17084 Filed 8-18-17; 8:45 am]
BILLING CODE 4910-13-P
