Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters, 20341-20344 [2021-07800]
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Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules
safety cable, the correct installation of lock
wire 0.20 CRES NAS 33540 P/N
MS20995C20 (double-twist lock wire), and
any missing double-twist lock wire for each
set of upper (connecter) end and lower
(pigtail or standpipe) end fasteners of the M/
R slip ring as depicted in Figures 1 and 2 of
Annex A to Leonardo Helicopters Alert
Service Bulletin (ASB) No. 139–472, dated
May 9, 2017 (ASB 139–472), or Leonardo
Helicopters ASB No. 189–138, dated May 12,
2017 (ASB 189–138), as applicable to your
model helicopter. Figures 2 and 3 of Annex
A to ASB 139–472 and ASB 189–138 also
show examples of a ferrule ended safety
cable installed that are not approved.
Note 1 to paragraph (g)(1)(i): Annex A to
ASB 139–472 and ASB 189–138 is Moog
Service Bulletin No. SB 16–01, Revision 5,
undated.
(ii) If all of the screws are present, there is
not any ferrule ended safety cable installed,
the double-twist lock wire is correctly
installed, and none of the double-twist lock
wire is missing on each set of upper end and
lower end fasteners of the M/R slip ring,
before further flight, mark the letter ‘‘L’’
following the S/N on the identification label
by following the Compliance Instructions,
paragraph 3) of Annex A to ASB 139–472 or
ASB 189–138, as applicable to your model
helicopter.
(iii) If a screw is missing from the inner
diameter (the connector flange) of the upper
end of the M/R slip ring, before further flight,
remove the M/R slip ring from service.
(iv) If a screw is missing from the outer
diameter of the upper end, from the inner
diameter of the lower end (shaft extension
attachment area), or from the outer diameter
of the lower end, before further flight, install
a new screw and washer, apply a torque to
1–1.25 Nm, and install double-twist lock
wire by following the Compliance
Instructions, paragraphs 9)a) through g) of
Annex A to ASB 139–472 or ASB 189–138,
as applicable to your model helicopter.
(v) If any double-twist lock wire is not
correctly installed, is missing, or if there is
a ferrule ended safety cable installed on any
set of upper end or lower end fasters of the
M/R slip ring, before further flight, remove
the incorrectly installed lock wire or ferrule
ended safety cable from service, as
applicable, and inspect the fastener torque by
applying 1–1.25 Nm of torque.
(A) If the torque of a screw installed in the
inner diameter (the connector flange) of the
upper end of the M/R slip ring is below 1 Nm
of torque, do not remove or replace the
screw, before further flight, apply a torque of
1–1.25 Nm.
(B) If the torque of a screw installed in the
outer diameter of the upper end, in the inner
diameter of the lower end (shaft extension
attachment area), or in the outer diameter of
the lower end is below 1 Nm of torque, before
further flight, remove the affected screw and
washer from service, install a new screw and
washer, and apply a torque of 1–1.25 Nm.
(C) Install double-twist lock wire by
following the Compliance Instructions,
paragraphs 9)a) through g) of Annex A to
ASB 139–472 or ASB 189–138, as applicable
to your model helicopter.
(vi) Mark the letter ‘‘L’’ following the S/N
on the identification label by following the
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Compliance Instructions, paragraph 3) of
Annex A to ASB 139–472 or ASB 189–138,
as applicable to your model helicopter.
(2) As of the effective date of this AD, do
not install an M/R slip ring identified in
paragraph (c) of this AD unless the
requirements of paragraph (g)(1) have been
accomplished.
DEPARTMENT OF TRANSPORTATION
(h) Special Flight Permits
RIN 2120–AA64
Special flight permits are prohibited.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
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 International Validation
Branch, send it to the attention of the person
identified in paragraph (j)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@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.
(j) Related Information
(1) For more information about this AD,
contact Steven Warwick, Aerospace
Engineer, Certification Section, Fort Worth
ACO Branch, Compliance & Airworthiness
Division, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone (817) 222–5225; email
steven.r.warwick@faa.gov.
(2) Moog Service Bulletin No. SB 16–01,
Revision 5, undated, is attached as Annex A
to both ASB 139–472 and ASB 189–138. For
Leonardo Helicopters and Moog service
information identified in this AD, contact
Leonardo S.p.A. Helicopters, Emanuele
Bufano, Head of Airworthiness, Viale
G.Agusta 520, 21017 C.Costa di Samarate
(Va) Italy; telephone +39–0331–225074; fax
+39–0331–229046; or at https://
www.leonardocompany.com/en/home. You
may view the referenced service information
at the 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.
(3) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2017–0083, dated May 10, 2017,
and EASA AD 2017–0087, dated May 12,
2017. You may view the EASA ADs on the
internet at https://www.regulations.gov in the
AD Docket.
Issued on April 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–07666 Filed 4–16–21; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0308; Project
Identifier MCAI–2020–00594–R]
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH (AHD)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Helicopters Deutschland
GmbH (AHD) Model BO–105A, BO–
105C, BO–105S, and BO–105LS A–3
helicopters equipped with a certain
hoist system. This AD was prompted by
an uncommanded activation of the hoist
cable cutter function on an MBB–BK117
C–1 helicopter, which prompted a
design review of the BO105 hoist
control grip with coiled cable. This
proposed AD would require inspections
of the hoist control grip with coiled
cable and deactivation of the hoist cuter
function, as specified in a European
Aviation Safety Agency (now European
Union Aviation Safety Agency) (EASA)
AD, which is proposed for incorporation
by reference (IBR). 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 June 3, 2021.
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 material that is proposed for IBR
in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
material on the EASA website at https://
ad.easa.europa.eu. You may view this
material at the FAA, Office of the
SUMMARY:
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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. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0308.
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–2021–
0308; 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 NPRM, 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 FURTHER INFORMATION CONTACT:
Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division,
3960 Paramount Blvd., Lakewood, CA
90712; telephone (562) 627–5371; email
blaine.williams@faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0308; Project Identifier
MCAI–2020–00594–R’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this proposal.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
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comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Blaine Williams,
Aerospace Engineer, Cabin Safety &
Environmental Systems Section, Los
Angeles ACO Branch, Compliance &
Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5371; email
blaine.williams@faa.gov. Any
commentary that the FAA receives that
is not specifically designated as CBI will
be placed in the public docket for this
rulemaking.
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2015–0017, dated February 4, 2015
(EASA AD 2015–0017) to correct an
unsafe condition for all Airbus
Helicopters Deutschland GmbH Model
BO105 A, BO105 C, BO105 D, BO105 S
and BO105 LS A–3 helicopters.
This proposed AD was prompted by
uncommanded activation of the hoist
cable cutter function on an MBB–BK117
C–1 helicopter which prompted a
design review of the BO105 hoist
control grip with coiled cable. It was
determined that mechanical damage in
the harness of the control grip could
cause an uncommanded deployment of
the cable cutter function. The FAA is
proposing this AD to prevent
uncommanded cutting of the hoist cable
and subsequent injury to persons being
lifted by the hoist and injury to persons
on the ground. See the EASA AD for
additional background information.
Related Service Information Under 1
CFR Part 51
For Model BO105 C, BO105 D, BO105
S and BO105 LS A–3 helicopters, EASA
AD 2015–0017 specifies to perform an
initial and recurring inspections of the
hoist control grip with coiled cable of
the hoist and depending on the results,
replacing the hoist control grip with
coiled cable with a serviceable part.
EASA also specifies to replace any hoist
control grip with coiled cable that has
exceeded 10 years since first installation
or since last overhaul and to deactivate
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the cable cutter function in accordance
with referenced service information.
EASA AD 2015–0017 also specifies to
not operate the hoist on any of the
model BO105 A, BO105 D, variant
BO105 D, and BO105 DS helicopters.
For most BO105 model helicopters,
except for BO105 D, variant BO105 D,
and BO105 DS model helicopters, EASA
specifies to amend the helicopter flight
manual (FM) to incorporate the
temporary revision as specified in Table
1 of the EASA AD.
This material 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
These products have been approved
by the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to the
bilateral agreement with the State of
Design Authority, the FAA has been
notified of the unsafe condition
described in the EASA AD referenced
above. The FAA is proposing this AD
after evaluating all the relevant
information and determining the unsafe
condition described previously is likely
to exist or develop in other products of
these same type designs.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
EASA AD 2015–0017, described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this proposed AD and
except as discussed under ‘‘Differences
Between this Proposed AD and the
EASA AD.’’ Additionally, the owner/
operator (pilot) may perform the
required visual checks but must enter
compliance with the applicable
paragraph of this AD in the helicopter
maintenance records in accordance with
14 CFR 43.9(a)(1) through (4) and
91.417(a)(2)(v). A pilot may perform
these checks because they only involve
visually checking affected control grips
with coiled cable. This action can be
performed equally well by a pilot or a
mechanic. This check is an exception to
the FAA’s standard maintenance
regulations.
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA initially worked with
Airbus and EASA to develop a process
to use certain EASA ADs as the primary
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source of information for compliance
with requirements for corresponding
FAA ADs. The FAA has since
coordinated with other manufacturers
and civil aviation authorities (CAAs) to
use this process. As a result, EASA AD
2015–0017 will be incorporated by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2015–0017
in its entirety, through that
incorporation, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
Using common terms that are the same
as the heading of a particular section in
the EASA AD does not mean that
operators need comply only with that
section. For example, where the AD
requirement refers to ‘‘all required
actions and compliance times,’’
compliance with this AD requirement is
not limited to the section titled
‘‘Required Action(s) and Compliance
Time(s)’’ in the EASA AD. Service
information specified in EASA AD
2015–0017 that is required for
compliance with EASA AD 2015–0017
will be available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0308 after the FAA final
rule is published.
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Differences Between This Proposed AD
and the EASA AD
Where EASA AD 2015–0017 refers to
its effective date, this proposed AD
requires using the effective date of the
FAA AD. Where EASA AD 2015–0017
specifies this unsafe condition for
Airbus Helicopters Deutschland GmbH
Model BO105 A, BO105 C, BO105 D,
BO105 S and BO105 LS A–3
helicopters, this proposed AD will not
include Model BO–105 D helicopters,
because this model is not FAA typecertificated. Where EASA AD 2015–
0017 specifies replacing an affected
part, this proposed AD requires
removing the part from service. Where
the service information referenced in
the EASA AD refers to calendar time for
certain actions, this proposed AD uses
hours time-in-service instead. The
EASA AD allows a tolerance to certain
compliance times, whereas this
proposed AD does not. The EASA AD
requires using service information to
accomplish the preflight checks of the
control grip with coil cable, whereas
this proposed AD would require
visually checking the condition of the
control grip and coiled cable for
mechanical damage including deformed
or damaged switches, damaged housing,
abrasion, cracks, and cuts instead.
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Interim Action
The FAA considers this proposed AD
interim action. If final action is later
identified, the FAA might consider
further rulemaking then.
Costs of Compliance
The FAA estimates that this AD
affects 20 helicopters of U.S. Registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates that operators may incur
the following costs in order to comply
with this proposed AD.
Inspecting the hoist control grip with
coiled cable would take up to one
quarter work-hour(s) for an estimated
cost of $21 per helicopter and $420 for
the U.S. fleet, per inspection cycle.
Replacing the hoist control grip
would take about 1 work-hour and parts
cost $1,956 for an estimated cost of
$2,041 per helicopter.
Replacing the coiled cable would take
about 2 work-hours and parts cost
$1,858 for an estimated cost of $2,028
per helicopter.
Deactivation of the cable cutter
function would take about 1 work hour
and parts would cost about $26 for an
estimated cost $111 per hoist control
grip.
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.
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For the reasons discussed above, 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.
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:
■
Airbus Helicopters Deutschland GmbH
(AHD): Docket No. FAA–2021–0308;
Project Identifier MCAI–2020–00594–R.
(a) Comments Due Date
The FAA must receive comments by June
3, 2021.
(b) Affected Airworthiness Directives (ADs)
None.
(c) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH (AHD) Model BO–105A,
BO–105C, BO–105S, and BO–105LS A–3
helicopters, certificated in any category, as
identified in European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD 2015–0017 dated
February 4, 2015 (EASA AD 2015–0017).
(d) Subject
Joint Aircraft System Component (JASC)
Code: 2500, Cabin Equipment/Furnishings.
(e) Reason
This AD was prompted by uncommanded
activation of the hoist cable cutter function
on an MBB–BK117 C–1 helicopter which
prompted a design review of the BO105 hoist
control grip with coiled cable. The FAA is
issuing this AD to prevent uncommanded
cutting of the hoist cable and subsequent
injury to persons being lifted by the hoist and
injury to persons on the ground.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2015–0017.
(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.
(h) Exceptions to EASA AD 2015–0017
(1) Where EASA AD 2015–0017 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where Note 1 of EASA AD 2015–0017
specifies a non-cumulative compliance time
tolerance of 10% for certain required
compliance times, this AD does not allow
this tolerance.
(3) Where paragraph (1) of EASA AD 2015–
0017 specifies a compliance time of ‘‘not to
exceed 30 days’’, this AD requires a
compliance time of within 13 hours time-inservice.
(4) Where paragraph (4) of EASA AD 2015–
0017 specifies a compliance time of ‘‘within
9 months’’, this AD requires a compliance
time of within 108 hours time-in-service.
(5) Where paragraph (5) of EASA AD 2015–
0017 specifies a compliance time of ‘‘within
3 months’’, this AD requires a compliance
time of within 36 hours time-in-service.
(6) Where paragraph (3) of EASA AD 2015–
0017 specifies replacing a part with a
serviceable part, this AD requires removing
the part from service.
(7) Where the service information
referenced in EASA AD 2015–0017 specifies
to use tooling, equivalent tooling may be
used.
(8) Where the service information
referenced in paragraph (2) of EASA AD
2015–0017 specifies a visual check of the
control grip coiled cable, this AD requires,
before next flight after the effective date of
this AD involving a hoist operation, visually
checking the control grip with coiled cable
for mechanical damage including deformed
or damaged switches, damaged housing,
abrasion, cracks, and cuts. These visual
checks may be performed by the owner/
operator (pilot) holding at least a private pilot
certificate and must be entered into the
aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9(a)(1)
through (4) and 14 CFR 91.417(a)(2)(v). The
record must be maintained as required by 14
CFR 91.417, 121.380, or 135.439.
(9) Where EASA AD 2015–0017 refers to
November 10, 2014, the effective date of
EASA AD 2014–0235, this AD requires using
the effective date of this AD.
(10) The ‘‘Remarks’’ section of EASA AD
2015–0017 does not apply to this AD.
(j) Related Information
(1) For EASA AD 2015–0017, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this
material at the 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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0308.
(2) For more information about this AD,
contact Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5371; email
blaine.williams@faa.gov.
Issued on April 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
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 International Validation
Branch, send it to the attention of the person
identified in paragraph (j)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
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BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2019–0824]
RIN 1625–AA09
Drawbridge Operation Regulation;
Milwaukee, Menomonee, and
Kinnickinnic Rivers and Burnham
Canals, Milwaukee, WI
Coast Guard, DHS.
Notice of proposed rulemaking.
AGENCY:
ACTION:
The Coast Guard proposes to
change the operating schedules of the
bridges over the Milwaukee,
Menomonee, and Kinnickinnic Rivers
and South Menomonee and Burnham
Canals. The City of Milwaukee
requested the regulations to be reviewed
and updated to allow for a more
balanced flow of maritime and land
based transportation.
DATES: Comments and relate material
must reach the Coast Guard on or before
June 18, 2021.
ADDRESSES: You may submit comments
identified by docket number USCG–
SUMMARY:
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
2019–0824 using Federal e-Rulemaking
Portal at https://www.regulations.gov.
See the ‘‘Public Participation and
Request for Comments’’ portion of the
SUPPLEMENTARY INFORMATION section
below for instructions on submitting
comments.
If
you have questions on this proposed
rule, call or email Mr. Lee D. Soule,
Bridge Management Specialist, Ninth
Coast Guard District; telephone 216–
902–6085, email Lee.D.Soule@uscg.mil.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
I. Table of Abbreviations
CFR Code of Federal Regulations
DHS Department of Homeland Security
FR Federal Register
IGLD85 International Great Lakes Datum of
1985
LWD Low Water Datum based on IGLD85
OMB Office of Management and Budget
NPRM Notice of Proposed Rulemaking
(Advance, Supplemental)
§ Section
U.S.C. United States Code
II. Background, Purpose and Legal
Basis
The Milwaukee River is
approximately 104 miles long.
Beginning in Fond du Lac County the
river flows easterly to a low head dam
just above the Humboldt Avenue Bridge
at mile 3.22 in downtown Milwaukee,
WI. From here the river flows south to
Lake Michigan. This southerly course of
the Milwaukee River divides the
lakefront area from the rest of the city.
The Menomonee River joins the
Milwaukee River at Mile 1.01 with the
Kinnickinnic River joining the
Milwaukee River at Mile 0.39. 21
bridges cross the Milwaukee River from
mile 0.19 to mile 3.22. In the early 20th
Century, the Milwaukee River was
heavily used to support the industries in
and around the Great Lakes. Today, the
river has been redeveloped as a tourist
and recreational destination. From its
confluence with the Milwaukee River
the Menomonee River flows west for 33
miles. The lower three miles of the
Menomonee River is passable by vessels
over 600 feet in length. Seven bridges
cross the navigable portion of the
Menomonee River.
The South Menomonee Canal and the
Burnham Canal were both excavated
during a waterways improvement
project in 1864. Both man-made canals
are tributaries of the Menomonee River
branching just above its mouth. The
South Menomonee Canal is crossed by
two bridges and the Burnham Canal is
crossed by three bridges. The
Kinnickinnic River flows north through
the southern portion of the City of
E:\FR\FM\19APP1.SGM
19APP1
]]>Agencies
[Federal Register Volume 86, Number 73 (Monday, April 19, 2021)]
[Proposed Rules]
[Pages 20341-20344]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-07800]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0308; Project Identifier MCAI-2020-00594-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(AHD) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A,
BO-105C, BO-105S, and BO-105LS A-3 helicopters equipped with a certain
hoist system. This AD was prompted by an uncommanded activation of the
hoist cable cutter function on an MBB-BK117 C-1 helicopter, which
prompted a design review of the BO105 hoist control grip with coiled
cable. This proposed AD would require inspections of the hoist control
grip with coiled cable and deactivation of the hoist cuter function, as
specified in a European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD, which is proposed for incorporation
by reference (IBR). 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 June 3,
2021.
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 material that is proposed for IBR in this AD, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999
000; email [email protected]; internet www.easa.europa.eu. You may
find this material on the EASA website at https://ad.easa.europa.eu.
You may view this material at the FAA, Office of the
[[Page 20342]]
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. It is also available in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2021-0308.
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-2021-
0308; 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 NPRM, 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 FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA
90712; telephone (562) 627-5371; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0308; Project Identifier
MCAI-2020-00594-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposal.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental
Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness
Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562)
627-5371; email [email protected]. Any commentary that the FAA
receives that is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Discussion
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2015-0017, dated February 4, 2015
(EASA AD 2015-0017) to correct an unsafe condition for all Airbus
Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S
and BO105 LS A-3 helicopters.
This proposed AD was prompted by uncommanded activation of the
hoist cable cutter function on an MBB-BK117 C-1 helicopter which
prompted a design review of the BO105 hoist control grip with coiled
cable. It was determined that mechanical damage in the harness of the
control grip could cause an uncommanded deployment of the cable cutter
function. The FAA is proposing this AD to prevent uncommanded cutting
of the hoist cable and subsequent injury to persons being lifted by the
hoist and injury to persons on the ground. See the EASA AD for
additional background information.
Related Service Information Under 1 CFR Part 51
For Model BO105 C, BO105 D, BO105 S and BO105 LS A-3 helicopters,
EASA AD 2015-0017 specifies to perform an initial and recurring
inspections of the hoist control grip with coiled cable of the hoist
and depending on the results, replacing the hoist control grip with
coiled cable with a serviceable part. EASA also specifies to replace
any hoist control grip with coiled cable that has exceeded 10 years
since first installation or since last overhaul and to deactivate the
cable cutter function in accordance with referenced service
information.
EASA AD 2015-0017 also specifies to not operate the hoist on any of
the model BO105 A, BO105 D, variant BO105 D, and BO105 DS helicopters.
For most BO105 model helicopters, except for BO105 D, variant BO105 D,
and BO105 DS model helicopters, EASA specifies to amend the helicopter
flight manual (FM) to incorporate the temporary revision as specified
in Table 1 of the EASA AD.
This material 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
These products have been approved by the aviation authority of
another country, and is approved for operation in the United States.
Pursuant to the bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the EASA
AD referenced above. The FAA is proposing this AD after evaluating all
the relevant information and determining the unsafe condition described
previously is likely to exist or develop in other products of these
same type designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in EASA AD 2015-0017, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this proposed AD and except as discussed under
``Differences Between this Proposed AD and the EASA AD.'' Additionally,
the owner/operator (pilot) may perform the required visual checks but
must enter compliance with the applicable paragraph of this AD in the
helicopter maintenance records in accordance with 14 CFR 43.9(a)(1)
through (4) and 91.417(a)(2)(v). A pilot may perform these checks
because they only involve visually checking affected control grips with
coiled cable. This action can be performed equally well by a pilot or a
mechanic. This check is an exception to the FAA's standard maintenance
regulations.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA initially worked with Airbus and EASA to develop a
process to use certain EASA ADs as the primary
[[Page 20343]]
source of information for compliance with requirements for
corresponding FAA ADs. The FAA has since coordinated with other
manufacturers and civil aviation authorities (CAAs) to use this
process. As a result, EASA AD 2015-0017 will be incorporated by
reference in the FAA final rule. This proposed AD would, therefore,
require compliance with EASA AD 2015-0017 in its entirety, through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this proposed AD. Using common terms that are
the same as the heading of a particular section in the EASA AD does not
mean that operators need comply only with that section. For example,
where the AD requirement refers to ``all required actions and
compliance times,'' compliance with this AD requirement is not limited
to the section titled ``Required Action(s) and Compliance Time(s)'' in
the EASA AD. Service information specified in EASA AD 2015-0017 that is
required for compliance with EASA AD 2015-0017 will be available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0308 after the FAA final rule is published.
Differences Between This Proposed AD and the EASA AD
Where EASA AD 2015-0017 refers to its effective date, this proposed
AD requires using the effective date of the FAA AD. Where EASA AD 2015-
0017 specifies this unsafe condition for Airbus Helicopters Deutschland
GmbH Model BO105 A, BO105 C, BO105 D, BO105 S and BO105 LS A-3
helicopters, this proposed AD will not include Model BO-105 D
helicopters, because this model is not FAA type-certificated. Where
EASA AD 2015-0017 specifies replacing an affected part, this proposed
AD requires removing the part from service. Where the service
information referenced in the EASA AD refers to calendar time for
certain actions, this proposed AD uses hours time-in-service instead.
The EASA AD allows a tolerance to certain compliance times, whereas
this proposed AD does not. The EASA AD requires using service
information to accomplish the preflight checks of the control grip with
coil cable, whereas this proposed AD would require visually checking
the condition of the control grip and coiled cable for mechanical
damage including deformed or damaged switches, damaged housing,
abrasion, cracks, and cuts instead.
Interim Action
The FAA considers this proposed AD interim action. If final action
is later identified, the FAA might consider further rulemaking then.
Costs of Compliance
The FAA estimates that this AD affects 20 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this proposed AD.
Inspecting the hoist control grip with coiled cable would take up
to one quarter work-hour(s) for an estimated cost of $21 per helicopter
and $420 for the U.S. fleet, per inspection cycle.
Replacing the hoist control grip would take about 1 work-hour and
parts cost $1,956 for an estimated cost of $2,041 per helicopter.
Replacing the coiled cable would take about 2 work-hours and parts
cost $1,858 for an estimated cost of $2,028 per helicopter.
Deactivation of the cable cutter function would take about 1 work
hour and parts would cost about $26 for an estimated cost $111 per
hoist control grip.
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 above, 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.
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:
Airbus Helicopters Deutschland GmbH (AHD): Docket No. FAA-2021-0308;
Project Identifier MCAI-2020-00594-R.
(a) Comments Due Date
The FAA must receive comments by June 3, 2021.
(b) Affected Airworthiness Directives (ADs)
None.
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH (AHD)
Model BO-105A, BO-105C, BO-105S, and BO-105LS A-3 helicopters,
certificated in any category, as identified in European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
2015-0017 dated February 4, 2015 (EASA AD 2015-0017).
(d) Subject
Joint Aircraft System Component (JASC) Code: 2500, Cabin
Equipment/Furnishings.
(e) Reason
This AD was prompted by uncommanded activation of the hoist
cable cutter function on an MBB-BK117 C-1 helicopter which prompted
a design review of the BO105 hoist control grip with coiled cable.
The FAA is issuing this AD to prevent uncommanded cutting of the
hoist cable and subsequent injury to persons being lifted by the
hoist and injury to persons on the ground.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 20344]]
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2015-0017.
(h) Exceptions to EASA AD 2015-0017
(1) Where EASA AD 2015-0017 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where Note 1 of EASA AD 2015-0017 specifies a non-cumulative
compliance time tolerance of 10% for certain required compliance
times, this AD does not allow this tolerance.
(3) Where paragraph (1) of EASA AD 2015-0017 specifies a
compliance time of ``not to exceed 30 days'', this AD requires a
compliance time of within 13 hours time-in-service.
(4) Where paragraph (4) of EASA AD 2015-0017 specifies a
compliance time of ``within 9 months'', this AD requires a
compliance time of within 108 hours time-in-service.
(5) Where paragraph (5) of EASA AD 2015-0017 specifies a
compliance time of ``within 3 months'', this AD requires a
compliance time of within 36 hours time-in-service.
(6) Where paragraph (3) of EASA AD 2015-0017 specifies replacing
a part with a serviceable part, this AD requires removing the part
from service.
(7) Where the service information referenced in EASA AD 2015-
0017 specifies to use tooling, equivalent tooling may be used.
(8) Where the service information referenced in paragraph (2) of
EASA AD 2015-0017 specifies a visual check of the control grip
coiled cable, this AD requires, before next flight after the
effective date of this AD involving a hoist operation, visually
checking the control grip with coiled cable for mechanical damage
including deformed or damaged switches, damaged housing, abrasion,
cracks, and cuts. These visual checks may be performed by the owner/
operator (pilot) holding at least a private pilot certificate and
must be entered into the aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be maintained as required by 14 CFR
91.417, 121.380, or 135.439.
(9) Where EASA AD 2015-0017 refers to November 10, 2014, the
effective date of EASA AD 2014-0235, this AD requires using the
effective date of this AD.
(10) The ``Remarks'' section of EASA AD 2015-0017 does not apply
to this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation 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 International Validation Branch, send
it to the attention of the person identified in paragraph (j)(2) of
this AD. Information may be emailed to: [email protected].
(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.
(j) Related Information
(1) For EASA AD 2015-0017, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu. You may
view this material at the 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. This material may be found in the AD docket
on the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0308.
(2) For more information about this AD, contact Blaine Williams,
Aerospace Engineer, Cabin Safety & Environmental Systems Section,
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712; telephone (562) 627-5371; email
[email protected].
Issued on April 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-07800 Filed 4-16-21; 8:45 am]
BILLING CODE 4910-13-P
