Airworthiness Directives; Airbus Helicopters, 48366-48368 [2018-20487]
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<![CDATA[
48366
Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations
describes the unsafe condition as cracking
found in the wing rear spar web at the wing
station (WS) where the flap outboard hinge
is attached. We are issuing this AD to detect
and correct cracks in the wing rear spars and
the flap/aileron hinge arm support brackets.
This condition, if not corrected, could result
in structural failure with consequent loss of
control of the airplane.
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(f) Actions and Compliance
Unless already done, do the actions in
paragraphs (f)(1) through (5) of this AD:
(1) Within 400 hours time-in-service (TIS)
after October 30, 2018 (the effective date of
this AD) or within 6 months after October 30,
2018 (the effective date of this AD),
whichever occurs first, visually inspect the
left-hand and right-hand wing rear spar and
flap/aileron hinge arm support brackets by
following the Accomplishment Instructions
of Viking DHC–2 Beaver Service Bulletin
Number: V2/0009, Revision A, dated
February 10, 2017 (SB V2/0009, Revision A).
(2) For airplanes with an agricultural
configuration installed (SOO Mod 2/984),
within 400 hours TIS after October 30, 2018
(the effective date of this AD) or within 6
months after October 30, 2018 (the effective
date of this AD), whichever occurs first,
inspect the exterior store support arm bracket
at WS 101.24 by following the
Accomplishment Instructions of SB V2/0009,
Revision A.
(3) If any discrepancies are found during
the inspections required in paragraphs (f)(1)
and (2) of this AD, before further flight, repair
or replace using a method approved by the
Manager, New York ACO Branch, FAA;
Transport Canada; or Viking Air Limited’s
Transport Canada Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(4) Within 30 days after completing the
inspections required in paragraphs (f)(1) and
(2) of this AD, using the Operator Reply Form
on page 7 of SB V2/0009, Revision A, report
the inspection results to Viking Air Limited
at the address specified in paragraph (i)(3) of
this AD.
(5) As of October 30, 2018 (the effective
date of this AD), do not install a wing on any
airplane affected by this AD unless it has
been inspected as specified in paragraphs
(f)(1) of this AD and paragraph (f)(2) of this
AD, if applicable, and is found free of any
discrepancies.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Aziz Ahmed,
Aerospace Engineer, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone: (516)
228–7329; fax: (516) 794–5531; email:
aziz.ahmed@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
VerDate Sep<11>2014
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Jkt 244001
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO Branch,
FAA; or Transport Canada; or Viking Air
Limited’s Transport Canada DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a currently
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 1 hour per response,
including the time for reviewing instructions,
searching existing data sources, gathering
and maintaining the data needed, completing
and reviewing the collection of information.
All responses to this collection of
information are mandatory. Send comments
regarding this burden estimate or any other
aspect of this collection of information,
including suggestions for reducing this
burden to: Information Collection Clearance
Officer, Federal Aviation Administration,
10101 Hillwood Parkway, Fort Worth, TX
76177–1524.
(h) Related Information
Refer to MCAI Transport Canada AD
Number CF–2017–17, dated May 18, 2017,
for related information. You may examine the
MCAI on the internet at https://
www.regulations.gov/document?D=FAA2017-0867-0002.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) 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 this AD specifies otherwise.
(i) Viking DHC–2 Beaver Service Bulletin
Number: V2/0009, Revision A, dated
February 10, 2017.
(ii) Reserved.
(3) For Viking DHC–2 Beaver service
information identified in this AD, contact
Viking Air Limited Technical Support, 1959
De Havilland Way, Sidney, British Columbia,
Canada, V8L 5V5; telephone: (North
America) (800) 663–8444; fax: (250) 656–
0673; email: technical.support@
vikingair.com; internet: https://
www.vikingair.com/support/serviceBulletins.
(4) You may view this service information
at the FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148. In
addition, you can access this service
information on the internet at https://
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www.regulations.gov by searching for and
locating Docket No. FAA–2017–0867.
(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 Kansas City, Missouri, on
September 7, 2018
Melvin J. Johnson,
Aircraft Certification Service, Deputy
Director, Policy and Innovation Division,
AIR–601.
[FR Doc. 2018–20802 Filed 9–24–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0438; Product
Identifier 2017–SW–062–AD; Amendment
39–19410; AD 2018–19–10]
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 Model AS355E, AS355F,
AS355F1, AS355F2, and AS355N
helicopters. This AD requires measuring
a vibration level in the tail rotor (T/R)
drive. This AD was prompted by reports
of bearing degradation. The actions of
this AD are intended to prevent an
unsafe condition on these helicopters.
DATES: This AD is effective October 30,
2018.
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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0438; or in person at Docket Operations
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Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations
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, the economic evaluation,
any comments received, and other
information. The street address for
Docket Operations (phone: 800–647–
5527) is 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: Rao
Edupuganti, Aviation Safety Engineer,
Regulations and Policy Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
rao.edupuganti@faa.gov.
SUPPLEMENTARY INFORMATION:
control of the helicopter. To address this
unsafe condition and as an interim
measure, the EASA AD requires two
vibration level measurements of the
forward portion of the tail rotor drive
line, one before and one after cleaning
the MGB oil cooler fan, and replacing
the bearings if excessive level or level
trends are detected. The EASA AD also
specifies that after the effective date of
the AD, only those MGB oil cooler fan
assembly bearings that are new or that
have passed the vibration level
measurements may be installed.
Discussion
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 the
EASA 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
the same type design and that air safety
and the public interest require adopting
the AD requirements as proposed.
On May 17, 2018, at 83 FR 22886, 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 Helicopters Model AS355E,
AS355F, AS355F1, AS355F2, and
AS355N helicopters. The NPRM
proposed to require measuring the T/R
drive vibration level without balancing,
cleaning the fan, and repeating the
vibration level measurement. If the
difference between the two amplitude
values is greater than 0.75 inch per
second (ips), the NPRM proposed to
require replacing each T/R fan bearing.
The proposed requirements were
intended to prevent degradation of the
main gearbox (MGB) oil cooler fan
bearing (bearing), which could result in
loss of MGB and engine oil cooling
function, loss of the rear transmission,
and subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
2017–0159, dated August 25, 2017,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Airbus Helicopters Model
AS355E, AS355F, AS355F1, AS355F2,
and AS355N helicopters. EASA advises
of two occurrences on Model AS355
military helicopters in which the MGB
bearing installed on the T/R drive shaft
experienced significant degradation.
EASA states that while investigation has
not determined the cause of the failures,
this condition may also occur on other
Model AS355 helicopters due to design
commonality. According to EASA, this
condition, if not detected and corrected,
could result in loss of MGB and engine
oil cooling function, loss of the rear
transmission, and subsequent loss of
VerDate Sep<11>2014
16:30 Sep 24, 2018
Jkt 244001
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
Interim Action
We consider this AD to be an interim
action. The manufacturer is currently
developing a terminating action for the
unsafe condition described in this AD.
If a terminating action is identified, we
may consider further rulemaking then.
Related Service Information
Airbus Helicopters has issued Alert
Service Bulletin No. AS355–05.00.77,
Revision 0, dated July 3, 2017, which
contains procedures for checking the
condition of the fan assembly bearings
by measuring the vibration levels of the
first section of the T/R drive.
Costs of Compliance
We estimate that this AD affects 104
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
At an average labor rate of $85 per
work-hour, measuring the vibration
levels requires about 5 work-hours, for
a cost of $425 per helicopter and
$44,200 for the U.S. fleet. If required,
replacing both fan assembly bearings
requires about 8 work-hours, and
required parts cost $1,064, for a cost of
$1,744 per helicopter.
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48367
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
1. The authority citation for part 39
continues to read as follows:
■
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48368
Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations
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):
■
2018–19–10 Airbus Helicopters:
Amendment 39–19410; Docket No.
FAA–2018–0438; Product Identifier
2017–SW–062–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS355E, AS355F, AS355F1, AS355F2,
and AS355N helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
degradation of a main gearbox (MGB) oil
cooler fan assembly bearing. This condition
could result in loss of MGB and engine oil
cooling function, loss of the rear
transmission, and subsequent loss of control
of the helicopter.
DEPARTMENT OF TRANSPORTATION
(1) Airbus Helicopters Alert Service
Bulletin No. AS355–05.00.77, Revision 0,
dated July 3, 2017, which is not incorporated
by reference, contains additional information
about the subject of this AD. For service
information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://www.helicopters.airbus.
com/website/en/ref/Technical-Support_
73.html. You may review a copy of the
service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2017–0159, dated August 25, 2017. You
may view the EASA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2018–0438.
(c) Effective Date
This AD becomes effective October 30,
2018.
(h) Subject
(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.
Issued in Fort Worth, Texas, on September
12, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
Joint Aircraft Service Component (JASC)
Code: 6510, Tail Rotor Driveshaft.
(e) Required Actions
(1) Within 165 hours time-in-service (TIS):
(i) Measure the tail rotor (T/R) drive
vibration level without balancing the T/R
drive, and record the amplitude value.
(ii) Clean the oil cooler fan.
(iii) Measure the T/R drive vibration level
without balancing the T/R drive, and record
the amplitude value.
(iv) Calculate the difference between the
two amplitude values. If the difference is
greater than 0.75 inch per second (ips), before
further flight, replace each oil cooler fan
assembly bearing.
(2) After the effective date of this AD, do
not install an oil cooler fan assembly bearing
with more than 0 hours TIS unless the
requirements of this AD have been
accomplished.
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(g) Additional Information
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, 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.
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16:30 Sep 24, 2018
Jkt 244001
[FR Doc. 2018–20487 Filed 9–24–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 91
[Docket No.: FAA–2018–0838; Amdt. No.
91–352]
RIN 2120–AL34
Amendment of the Prohibition Against
Certain Flights in the Pyongyang Flight
Information Region (FIR) (ZKKP)
Correction
In rule document 2018–20173
appearing on pages 47059–47065 in the
issue of September 18, 2018, make the
following correction:
On page 47061, in the second column,
in the third line, ‘‘September 18, 2010’’
should read ‘‘September 18, 2020’’.
[FR Doc. C1–2018–20173 Filed 9–24–18; 8:45 am]
BILLING CODE 1301–00–D
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Federal Aviation Administration
14 CFR Part 97
[Docket No. 31213; Amdt. No. 3817]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule establishes, amends,
suspends, or removes Standard
Instrument Approach Procedures
(SIAPs) and associated Takeoff
Minimums and Obstacle Departure
Procedures (ODPs) for operations at
certain airports. These regulatory
actions are needed because of the
adoption of new or revised criteria, or
because of changes occurring in the
National Airspace System, such as the
commissioning of new navigational
facilities, adding new obstacles, or
changing air traffic requirements. These
changes are designed to provide safe
and efficient use of the navigable
airspace and to promote safe flight
operations under instrument flight rules
at the affected airports.
DATES: This rule is effective September
25, 2018. The compliance date for each
SIAP, associated Takeoff Minimums,
and ODP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of September
25, 2018.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
SUMMARY:
For Examination
1. U.S. Department of Transportation,
Docket Ops-M30, 1200 New Jersey
Avenue SE, West Bldg., Ground Floor,
Washington, DC 20590–0001.
2. The FAA Air Traffic Organization
Service Area in which the affected
airport is located;
3. The office of Aeronautical
Navigation Products, 6500 South
MacArthur Blvd., Oklahoma City, OK
73169 or,
4. 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/code_of_federal_
regulations/ibr_locations.html.
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]]>Agencies
[Federal Register Volume 83, Number 186 (Tuesday, September 25, 2018)]
[Rules and Regulations]
[Pages 48366-48368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20487]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0438; Product Identifier 2017-SW-062-AD; Amendment
39-19410; AD 2018-19-10]
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 Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters. This AD requires measuring a vibration level in the tail
rotor (T/R) drive. This AD was prompted by reports of bearing
degradation. The actions of this AD are intended to prevent an unsafe
condition on these helicopters.
DATES: This AD is effective October 30, 2018.
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.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0438; or in person at Docket Operations
[[Page 48367]]
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, the economic evaluation, any comments received, and
other information. The street address for Docket Operations (phone:
800-647-5527) is 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: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Section, Rotorcraft Standards Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On May 17, 2018, at 83 FR 22886, 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 Helicopters Model
AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. The NPRM
proposed to require measuring the T/R drive vibration level without
balancing, cleaning the fan, and repeating the vibration level
measurement. If the difference between the two amplitude values is
greater than 0.75 inch per second (ips), the NPRM proposed to require
replacing each T/R fan bearing. The proposed requirements were intended
to prevent degradation of the main gearbox (MGB) oil cooler fan bearing
(bearing), which could result in loss of MGB and engine oil cooling
function, loss of the rear transmission, and subsequent loss of control
of the helicopter.
The NPRM was prompted by AD No. 2017-0159, dated August 25, 2017,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters. EASA advises of two occurrences on Model AS355 military
helicopters in which the MGB bearing installed on the T/R drive shaft
experienced significant degradation. EASA states that while
investigation has not determined the cause of the failures, this
condition may also occur on other Model AS355 helicopters due to design
commonality. According to EASA, this condition, if not detected and
corrected, could result in loss of MGB and engine oil cooling function,
loss of the rear transmission, and subsequent loss of control of the
helicopter. To address this unsafe condition and as an interim measure,
the EASA AD requires two vibration level measurements of the forward
portion of the tail rotor drive line, one before and one after cleaning
the MGB oil cooler fan, and replacing the bearings if excessive level
or level trends are detected. The EASA AD also specifies that after the
effective date of the AD, only those MGB oil cooler fan assembly
bearings that are new or that have passed the vibration level
measurements may be installed.
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
the EASA 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 the same type
design and that air safety and the public interest require adopting the
AD requirements as proposed.
Interim Action
We consider this AD to be an interim action. The manufacturer is
currently developing a terminating action for the unsafe condition
described in this AD. If a terminating action is identified, we may
consider further rulemaking then.
Related Service Information
Airbus Helicopters has issued Alert Service Bulletin No. AS355-
05.00.77, Revision 0, dated July 3, 2017, which contains procedures for
checking the condition of the fan assembly bearings by measuring the
vibration levels of the first section of the T/R drive.
Costs of Compliance
We estimate that this AD affects 104 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD.
At an average labor rate of $85 per work-hour, measuring the
vibration levels requires about 5 work-hours, for a cost of $425 per
helicopter and $44,200 for the U.S. fleet. If required, replacing both
fan assembly bearings requires about 8 work-hours, and required parts
cost $1,064, for a cost of $1,744 per helicopter.
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:
[[Page 48368]]
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):
2018-19-10 Airbus Helicopters: Amendment 39-19410; Docket No. FAA-
2018-0438; Product Identifier 2017-SW-062-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS355E, AS355F,
AS355F1, AS355F2, and AS355N helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as degradation of a main
gearbox (MGB) oil cooler fan assembly bearing. This condition could
result in loss of MGB and engine oil cooling function, loss of the
rear transmission, and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective October 30, 2018.
(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) Within 165 hours time-in-service (TIS):
(i) Measure the tail rotor (T/R) drive vibration level without
balancing the T/R drive, and record the amplitude value.
(ii) Clean the oil cooler fan.
(iii) Measure the T/R drive vibration level without balancing
the T/R drive, and record the amplitude value.
(iv) Calculate the difference between the two amplitude values.
If the difference is greater than 0.75 inch per second (ips), before
further flight, replace each oil cooler fan assembly bearing.
(2) After the effective date of this AD, do not install an oil
cooler fan assembly bearing with more than 0 hours TIS unless the
requirements of this AD have been accomplished.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, 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
(1) Airbus Helicopters Alert Service Bulletin No. AS355-
05.00.77, Revision 0, dated July 3, 2017, which is not incorporated
by reference, contains additional information about the subject of
this AD. For service information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or
at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review a copy of the service information at
the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2017-0159, dated August 25, 2017. You
may view the EASA AD on the internet at https://www.regulations.gov
in Docket No. FAA-2018-0438.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor
Driveshaft.
Issued in Fort Worth, Texas, on September 12, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-20487 Filed 9-24-18; 8:45 am]
BILLING CODE 4910-13-P
