Airworthiness Directives; Sikorsky Aircraft Corporation, 34838-34841 [2017-15222]
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34838
Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Rules and Regulations
of any record to which such person is
not entitled under the FOIA.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
PART 1003—IMPLEMENTATION OF
THE GOVERNMENT IN THE SUNSHINE
ACT
9. The authority citation for part 1003
continues to read as follows:
■
10. Amend § 1003.4 by revising
paragraph (c) and adding paragraphs (d)
through (f) to read as follows:
■
§ 1003.4 Procedures for public
announcement of meetings.
*
*
*
*
*
(c) When a meeting has been called by
the Chairman, the notice shall contain
such agenda items as the Chairman
designates. The notice shall be
circulated to Members in advance of
publication and Members, by majority
vote, may add additional agenda items.
(d) When a meeting is called by a
majority of Members, the notice shall
contain such agenda items as have been
approved by a majority of the Board.
(e) The Executive Director will ensure
that the final agenda for the meeting
conforms to the notice published in the
Federal Register.
(f) If public notice is provided by
means other than publication in the
Federal Register, notice will be
promptly submitted to the Federal
Register for publication.
■ 11. Revise § 1003.7 to read as follows:
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§ 1003.7 Changes following public
announcement.
(a) The time, place, and agenda items
of a meeting following the public
announcement described in § 1003.4, or
the determination of the Board to open
or close a meeting, or a portion thereof,
to the public may be changed following
public announcement only if:
(1) A majority of all members
determine by recorded vote that Board
business so requires and that no earlier
announcement of the change was
possible; and
(2) The Board publicly announces
such change and the vote of each
member thereon at the earliest
practicable time.
(b) Changes to the time, place and
agenda items of a meeting called by the
Chairman pursuant to § 1003.4(c) must
be made with the concurrence of the
Chairman, except that when Members
have, by majority vote, added additional
agenda items, the addition of those
agenda items does not require the
Chairman’s concurrence.
[FR Doc. 2017–15660 Filed 7–26–17; 8:45 am]
BILLING CODE 6820–B3–P
17:07 Jul 26, 2017
[Docket No. FAA–2017–0664; Directorate
Identifier 2016–SW–073–AD; Amendment
39–18947; AD 2017–14–03]
RIN 2120–AA64
Authority: 5 U.S.C. 552b.
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14 CFR Part 39
Jkt 241001
Airworthiness Directives; Sikorsky
Aircraft Corporation
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky)
Model S–92A helicopters. This AD
requires an inspection and reduces the
retirement lives of certain landing gear
components. This AD is prompted by a
revised analysis of the fatigue life of the
landing gear. The actions of this AD are
intended to prevent an unsafe condition
on these products.
DATES: This AD becomes effective
August 11, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of August 11, 2017.
We must receive comments on this
AD by September 25, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0664; 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, any incorporated by
reference service information, the
economic evaluation, any comments
received, and other information. The
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street address for the Docket Operations
Office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
For service information identified in
this final rule, contact Sikorsky Aircraft
Corporation, Customer Service
Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email:
wcs_cust_service_eng.gr-sik@lmco.com.
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–
0664.
FOR FURTHER INFORMATION CONTACT:
Dorie Resnik, Aviation Safety Engineer,
Boston Aircraft Certification Office,
Engine & Propeller Directorate, 1200
District Avenue, Burlington,
Massachusetts 01803; telephone (781)
238–7693; email dorie.resnik@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Discussion
We are adopting a new AD for
Sikorsky Model S–92A helicopters. This
AD is prompted by Sikorsky’s updated
fatigue analysis of the nose and main
landing gear as part of a supplier
transition project. The updated fatigue
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Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Rules and Regulations
analysis revealed that certain
components—main landing gear (MLG)
wheel axle part number (P/N) 2392–
2334–001, MLG and nose landing gear
(NLG) threaded hinge pin P/N 2392–
2311–003, NLG cylinder P/N 2392–
4006–005, NLG hinge pin P/N 2392–
4312–003, and landing gear actuator rod
end P/N 2392–0876–901—require a
reduced service life. Sikorsky updated
the airworthiness limitations schedule
accordingly and developed a recurring
visual and ultrasonic inspection of NLG
airframe fitting assembly P/N 92209–
01101–041 once it has accumulated
31,600 landing cycles.
Accordingly, this AD requires
inspecting and reducing the life limits
of these landing gear components. The
actions specified by this AD are
intended to detect and prevent cracks or
failure of any landing gear component,
which could result in damage and loss
of control of the helicopter.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of this same
type design.
Related Service Information Under 1
CFR Part 51
We reviewed Ultrasonic Inspection
Technique No. UT 5077, Revision 0,
dated July 25, 2014 (UT 5077). UT 5077
contains the inspection method,
equipment and materials, calibration,
and inspection procedure for
performing an ultrasonic inspection of
nose gear actuator fitting P/N 92209–
01101–101.
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.
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Other Related Service Information
We also reviewed Sikorsky S–92
Helicopter Alert Service Bulletin 92–
32–004, Basic Issue, dated January 30,
2015 (ASB). The ASB describes
procedures for conducting a visual
inspection of the NLG airframe fitting
assembly and an ultrasonic inspection
by following the procedures in UT 5077.
AD Requirements
This AD requires removing the
following components from service:
• Any MLG wheel axle P/N 2392–
2334–001 that has 22,300 or more
landing cycles.
• Any MLG or NLG threaded hinge
pin P/N 2392–2311–003 that has 26,100
or more landing cycles.
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17:07 Jul 26, 2017
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• Any NLG cylinder P/N 2392–4006–
005 that has 26,300 or more landing
cycles.
• Any NLG hinge pin P/N 2392–
4312–003 that has 26,700 or more
landing cycles.
• Any landing gear actuator rod end
P/N 2392–0876–901 that has 41,700 or
more landing cycles.
For helicopters that have 31,600 or
more landing cycles and an NLG
airframe fitting assembly P/N 92209–
01101–041 installed, this AD also
requires:
• Using a 10X or higher power
magnifying glass, inspecting each
bushing and all visible surfaces of
mating lug fittings adjacent to each
bushing for fretting, corrosion, wear,
and scratches.
• Replacing the NLG airframe fitting
assembly before further flight if there is
fretting, corrosion, wear, or a scratch
more than 0.0005 inch deep.
• Ultrasonic inspecting the NLG
actuator fitting and replacing the NLG
actuator fitting before further flight if
there are any anomalies.
Differences Between This AD and the
Service Information
The ASB requires a repetitive
inspection of the NLG airframe fitting
assemblies P/N 92209–01101–041 every
1,986 landing cycles; this AD does not.
Interim Action
We consider this AD to be an interim
action. We are currently considering
requiring a repetitive inspection of the
NLG airframe fitting assemblies P/N
92209–01101–041 that would occur
every 1,986 landing cycles. However,
the planned compliance time for the
inspections would allow enough time to
provide notice and opportunity for prior
public comment on the merits of the
repetitive inspections.
Costs of Compliance
We estimate that this AD will affect
80 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 hour:
• Replacing a wheel axle P/N 2392–
2334–001 will require 2 work-hours and
required parts cost $22,000, for a cost
per helicopter of $22,170.
• Replacing a MLG or NLG threaded
hinge pin P/N 2392–2311–003 will
require 1 work-hour and required parts
cost $3,800, for a cost per helicopter of
$3,885.
• Replacing a NLG cylinder P/N
2392–4006–005 will require 1 workhour and required parts cost $27,200,
for a cost per helicopter of $27,285.
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• Replacing a NLG hinge pin P/N
2392–4312–003 will require 1 workhour and required parts cost $4,400, for
a cost per helicopter of $4,485.
• Replacing a landing gear actuator
rod end P/N 2392–0876–901 will
require 1 work-hour and required parts
cost $900, for a cost per helicopter of
$985.
• Inspecting the NLG airframe fitting
assembly P/N 92209–01101–041 will
require 8 work-hours, and required parts
cost is minimal, for a cost of $680 per
helicopter and $54,400 for the U.S. fleet.
• If required, replacing a NLG
actuator fitting P/N 92209–01101–101
would require 70 work-hours, and
required parts cost $10,000, for a cost
per helicopter of $15,950.
FAA’s Justification and Determination
of the Effective Date
Providing an opportunity for public
comments prior to adopting these AD
requirements would delay
implementing the safety actions needed
to correct this known unsafe condition.
Therefore, we find that the risk to the
flying public justifies waiving notice
and comment prior to the adoption of
this rule because replacing the landing
gear components affected by the lifelimit reductions required by this AD
must be accomplished before further
flight.
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Rules and Regulations
Regulatory Findings
List of Subjects in 14 CFR Part 39
We determined that 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, 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.
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:
■
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):
■
2017–14–03 Sikorsky Aircraft Corporation
(Sikorsky): Amendment 39–18947;
Docket No. FAA–2017–0664; Directorate
Identifier 2016–SW–073–AD.
(a) Applicability
This AD applies to Sikorsky Model S–92A
helicopters, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
fatigue failure of the landing gear. This
condition could result in failure of the
landing gear and subsequent damage to and
loss of control of the helicopter.
(c) Effective Date
This AD becomes effective August 11,
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) Before further flight, remove from
service any part that has accumulated the
number of landing cycles listed in Table 1 to
paragraph (e)(1) of this AD. Thereafter,
remove from service any part before
accumulating the number of landing cycles
listed in Table 1 to paragraph (e)(1) of this
AD. For purposes of this AD, a landing cycle
is counted anytime the helicopter lifts off
into the air and then lands again regardless
of the duration of the landing and regardless
of whether the engine is shut down. If the
number of landing cycles in unknown,
multiply the number of hours time-in-service
by 4.5 to determine the number of landing
cycles.
TABLE 1 TO PARAGRAPH (e)(1) OF THIS AD
Part name
Part number
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Main landing gear (MLG) wheel axle ....................................................................................................
MLG or nose landing gear (NLG) threaded hinge pin ..........................................................................
NLG cylinder ..........................................................................................................................................
NLG hinge pin ........................................................................................................................................
Landing gear actuator rod end ..............................................................................................................
(2) For helicopters with 31,600 or more
landing cycles and an NLG airframe fitting
assembly P/N 92209–01101–041 installed,
before further flight:
(i) Using a 10X or higher power magnifying
glass, inspect each bushing (P/N 92209–
01101–102 and P/N 92209–01101–103) and
all visible surfaces of mating lug fittings
adjacent to each bushing for fretting,
corrosion, wear, and scratches. If there is
fretting, corrosion, wear, or a scratch more
than 0.0005 inch deep, replace the NLG
airframe fitting assembly before further flight.
(ii) Ultrasonic inspect each NLG actuator
fitting P/N 92209–01101–101 in accordance
with Sikorsky Ultrasonic Inspection
Technique No. UT 5077, Revision 0, dated
July 25, 2014 (UT 5077), except you are not
required to report to or contact Sikorsky. If
there are any anomalies or suspect
indications, replace the NLG actuator fitting
before further flight.
Note 1 to paragraph (e)(2)(ii) of this AD:
A copy of UT 5077 is attached to Sikorsky
S–92 Helicopter Alert Service Bulletin 92–
32–004, Basic Issue, dated January 30, 2015.
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17:07 Jul 26, 2017
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(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Dorie Resnik, Aviation Safety Engineer,
Boston Aircraft Certification Office, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, Massachusetts 01803; telephone
(781) 238–7693; email dorie.resnik@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
Sikorsky S–92 Helicopter Alert Service
Bulletin 92–32–004, Basic Issue, dated
January 30, 2015, which is not incorporated
by reference, contains additional information
about the subject of this AD. For service
information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer
Service Engineering, 124 Quarry Road,
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2392–2334–001
2392–2311–003
2392–4006–005
2392–4312–003
2392–0876–901
Life limit
22,300
26,100
26,300
26,700
41,700
landing
landing
landing
landing
landing
cycles.
cycles.
cycles.
cycles.
cycles.
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email: wcs_
cust_service_eng.gr-sik@lmco.com. You may
review this service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 3200 Main Landing Gear and 3220
Nose Landing Gear.
(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.
(i) Ultrasonic Inspection Technique No. UT
5077, Revision 0, dated July 25, 2014.
Note 2 to paragraph (i)(2)(i): Ultrasonic
Inspection Technique No. UT 5077, Revision
0, dated July 25, 2014, is an attachment to
Sikorsky S–92 Helicopter Alert Service
Bulletin 92–32–004, Basic Issue, dated
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January 30, 2015, which is not incorporated
by reference.
(ii) Reserved.
(3) For Sikorsky service information
identified in this AD, contact Sikorsky
Aircraft Corporation, Customer Service
Engineering, 124 Quarry Road, Trumbull, CT
06611; telephone 1–800–Winged–S or 203–
416–4299; email: wcs_cust_service_eng.grsik@lmco.com.
(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.
of certain publications listed in this AD
as of August 31, 2017.
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
telephone: 514–855–5000; fax: 514–
855–7401; email: thd.crj@
aero.bombardier.com; Internet: https://
www.bombardier.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 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–2016–
9304.
Issued in Fort Worth, Texas, on June 27,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9304; 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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 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:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone: 516–228–7318;
fax: 516–794–5531.
SUPPLEMENTARY INFORMATION:
[FR Doc. 2017–15222 Filed 7–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9304; Directorate
Identifier 2016–NM–028–AD; Amendment
39–18959; AD 2017–14–15]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–700–1A10
and BD–700–1A11 airplanes. This AD
was prompted by reports of aileron and
rudder control cables that may have
tensions that are beyond allowable
limits. This AD requires a revision to
the maintenance or inspection program
to incorporate certification maintenance
requirement tasks that introduce
functional tests of the control cable
tension. We are issuing this AD to
address the unsafe condition on these
products.
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SUMMARY:
This AD is effective August 31,
2017.
The Director of the Federal Register
approved the incorporation by reference
DATES:
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17:07 Jul 26, 2017
Jkt 241001
Examining the AD Docket
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
BD–700–1A10 and BD–700–1A11
airplanes. The NPRM published in the
Federal Register on November 7, 2016
(81 FR 78080). The NPRM was
prompted by reports of aileron and
rudder control cables that may have
tensions that are beyond allowable
limits. The NPRM proposed to require
revising the maintenance or inspection
program to incorporate certification
maintenance requirement tasks that
introduce functional tests of the control
cable tension. We are issuing this AD to
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34841
detect and correct out-of-tolerance
tension in the control cables, which,
with certain system failures and
environmental conditions, could result
in reduced controllability of the
airplane.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2016–06R1,
dated July 25, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier Model BD–700–
1A10 and BD–700–1A11 airplanes. The
MCAI states:
Recent in-service inspections have shown
that aileron and rudder control cables may
have tensions beyond allowable limits.
Review of the technical documentation found
that there are no maintenance tasks to detect
and rectify out-of-tolerance tensions on these
cables. Out of tolerance cables in
combinations with certain system failures
and environmental conditions could result in
the degraded aircraft controllability.
* * * [This Canadian] AD was issued to
mandate a revision to the approved
maintenance schedule [maintenance or
inspection program, as applicable] to
introduce cable tension check [e.g.,
functional test,] as [certification maintenance
requirement] tasks.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–9304.
This AD requires revisions to certain
operator maintenance documents to
include new actions (e.g., inspections).
Compliance with these actions is
required by 14 CFR 91.403(c). For
airplanes that have been previously
modified, altered, or repaired in the
areas addressed by this AD, the operator
may not be able to accomplish the
actions described in the revisions. In
this situation, to comply with 14 CFR
91.403(c), the operator must request
approval for an alternative method of
compliance according to paragraph (j)(1)
of this AD. The request should include
a description of changes to the required
actions that will ensure the continued
operational safety of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Reference the Latest Time
Limits/Maintenance Checks (TLMC)
General Revision Instead of the
Temporary Revision (TR)
Bombardier, Inc., and KACALP Flight
Operations requested that paragraph (g)
E:\FR\FM\27JYR1.SGM
27JYR1
Agencies
[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Rules and Regulations]
[Pages 34838-34841]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15222]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073-AD;
Amendment 39-18947; AD 2017-14-03]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This
AD requires an inspection and reduces the retirement lives of certain
landing gear components. This AD is prompted by a revised analysis of
the fatigue life of the landing gear. The actions of this AD are
intended to prevent an unsafe condition on these products.
DATES: This AD becomes effective August 11, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of August 11,
2017.
We must receive comments on this AD by September 25, 2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0664; 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, any incorporated by reference service information,
the economic evaluation, any comments received, and other information.
The street address for the Docket Operations Office (telephone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
For service information identified in this final rule, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299;
email: wcs_cust_service_eng.gr-sik@lmco.com. 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-
0664.
FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aviation Safety
Engineer, Boston Aircraft Certification Office, Engine & Propeller
Directorate, 1200 District Avenue, Burlington, Massachusetts 01803;
telephone (781) 238-7693; email dorie.resnik@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.
Discussion
We are adopting a new AD for Sikorsky Model S-92A helicopters. This
AD is prompted by Sikorsky's updated fatigue analysis of the nose and
main landing gear as part of a supplier transition project. The updated
fatigue
[[Page 34839]]
analysis revealed that certain components--main landing gear (MLG)
wheel axle part number (P/N) 2392-2334-001, MLG and nose landing gear
(NLG) threaded hinge pin P/N 2392-2311-003, NLG cylinder P/N 2392-4006-
005, NLG hinge pin P/N 2392-4312-003, and landing gear actuator rod end
P/N 2392-0876-901--require a reduced service life. Sikorsky updated the
airworthiness limitations schedule accordingly and developed a
recurring visual and ultrasonic inspection of NLG airframe fitting
assembly P/N 92209-01101-041 once it has accumulated 31,600 landing
cycles.
Accordingly, this AD requires inspecting and reducing the life
limits of these landing gear components. The actions specified by this
AD are intended to detect and prevent cracks or failure of any landing
gear component, which could result in damage and loss of control of the
helicopter.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of this same type design.
Related Service Information Under 1 CFR Part 51
We reviewed Ultrasonic Inspection Technique No. UT 5077, Revision
0, dated July 25, 2014 (UT 5077). UT 5077 contains the inspection
method, equipment and materials, calibration, and inspection procedure
for performing an ultrasonic inspection of nose gear actuator fitting
P/N 92209-01101-101.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Other Related Service Information
We also reviewed Sikorsky S-92 Helicopter Alert Service Bulletin
92-32-004, Basic Issue, dated January 30, 2015 (ASB). The ASB describes
procedures for conducting a visual inspection of the NLG airframe
fitting assembly and an ultrasonic inspection by following the
procedures in UT 5077.
AD Requirements
This AD requires removing the following components from service:
Any MLG wheel axle P/N 2392-2334-001 that has 22,300 or
more landing cycles.
Any MLG or NLG threaded hinge pin P/N 2392-2311-003 that
has 26,100 or more landing cycles.
Any NLG cylinder P/N 2392-4006-005 that has 26,300 or more
landing cycles.
Any NLG hinge pin P/N 2392-4312-003 that has 26,700 or
more landing cycles.
Any landing gear actuator rod end P/N 2392-0876-901 that
has 41,700 or more landing cycles.
For helicopters that have 31,600 or more landing cycles and an NLG
airframe fitting assembly P/N 92209-01101-041 installed, this AD also
requires:
Using a 10X or higher power magnifying glass, inspecting
each bushing and all visible surfaces of mating lug fittings adjacent
to each bushing for fretting, corrosion, wear, and scratches.
Replacing the NLG airframe fitting assembly before further
flight if there is fretting, corrosion, wear, or a scratch more than
0.0005 inch deep.
Ultrasonic inspecting the NLG actuator fitting and
replacing the NLG actuator fitting before further flight if there are
any anomalies.
Differences Between This AD and the Service Information
The ASB requires a repetitive inspection of the NLG airframe
fitting assemblies P/N 92209-01101-041 every 1,986 landing cycles; this
AD does not.
Interim Action
We consider this AD to be an interim action. We are currently
considering requiring a repetitive inspection of the NLG airframe
fitting assemblies P/N 92209-01101-041 that would occur every 1,986
landing cycles. However, the planned compliance time for the
inspections would allow enough time to provide notice and opportunity
for prior public comment on the merits of the repetitive inspections.
Costs of Compliance
We estimate that this AD will affect 80 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 hour:
Replacing a wheel axle P/N 2392-2334-001 will require 2
work-hours and required parts cost $22,000, for a cost per helicopter
of $22,170.
Replacing a MLG or NLG threaded hinge pin P/N 2392-2311-
003 will require 1 work-hour and required parts cost $3,800, for a cost
per helicopter of $3,885.
Replacing a NLG cylinder P/N 2392-4006-005 will require 1
work-hour and required parts cost $27,200, for a cost per helicopter of
$27,285.
Replacing a NLG hinge pin P/N 2392-4312-003 will require 1
work-hour and required parts cost $4,400, for a cost per helicopter of
$4,485.
Replacing a landing gear actuator rod end P/N 2392-0876-
901 will require 1 work-hour and required parts cost $900, for a cost
per helicopter of $985.
Inspecting the NLG airframe fitting assembly P/N 92209-
01101-041 will require 8 work-hours, and required parts cost is
minimal, for a cost of $680 per helicopter and $54,400 for the U.S.
fleet.
If required, replacing a NLG actuator fitting P/N 92209-
01101-101 would require 70 work-hours, and required parts cost $10,000,
for a cost per helicopter of $15,950.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments prior to adopting
these AD requirements would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because replacing the landing gear
components affected by the life-limit reductions required by this AD
must be accomplished before further flight.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
[[Page 34840]]
Regulatory Findings
We determined that 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, 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):
2017-14-03 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
18947; Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073-
AD.
(a) Applicability
This AD applies to Sikorsky Model S-92A helicopters,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue failure of the
landing gear. This condition could result in failure of the landing
gear and subsequent damage to and loss of control of the helicopter.
(c) Effective Date
This AD becomes effective August 11, 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) Before further flight, remove from service any part that has
accumulated the number of landing cycles listed in Table 1 to
paragraph (e)(1) of this AD. Thereafter, remove from service any
part before accumulating the number of landing cycles listed in
Table 1 to paragraph (e)(1) of this AD. For purposes of this AD, a
landing cycle is counted anytime the helicopter lifts off into the
air and then lands again regardless of the duration of the landing
and regardless of whether the engine is shut down. If the number of
landing cycles in unknown, multiply the number of hours time-in-
service by 4.5 to determine the number of landing cycles.
Table 1 to Paragraph (e)(1) of This AD
----------------------------------------------------------------------------------------------------------------
Part name Part number Life limit
----------------------------------------------------------------------------------------------------------------
Main landing gear (MLG) wheel axle............. 2392-2334-001 22,300 landing cycles.
MLG or nose landing gear (NLG) threaded hinge 2392-2311-003 26,100 landing cycles.
pin.
NLG cylinder................................... 2392-4006-005 26,300 landing cycles.
NLG hinge pin.................................. 2392-4312-003 26,700 landing cycles.
Landing gear actuator rod end.................. 2392-0876-901 41,700 landing cycles.
----------------------------------------------------------------------------------------------------------------
(2) For helicopters with 31,600 or more landing cycles and an
NLG airframe fitting assembly P/N 92209-01101-041 installed, before
further flight:
(i) Using a 10X or higher power magnifying glass, inspect each
bushing (P/N 92209-01101-102 and P/N 92209-01101-103) and all
visible surfaces of mating lug fittings adjacent to each bushing for
fretting, corrosion, wear, and scratches. If there is fretting,
corrosion, wear, or a scratch more than 0.0005 inch deep, replace
the NLG airframe fitting assembly before further flight.
(ii) Ultrasonic inspect each NLG actuator fitting P/N 92209-
01101-101 in accordance with Sikorsky Ultrasonic Inspection
Technique No. UT 5077, Revision 0, dated July 25, 2014 (UT 5077),
except you are not required to report to or contact Sikorsky. If
there are any anomalies or suspect indications, replace the NLG
actuator fitting before further flight.
Note 1 to paragraph (e)(2)(ii) of this AD: A copy of UT 5077 is
attached to Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-
004, Basic Issue, dated January 30, 2015.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Dorie Resnik,
Aviation Safety Engineer, Boston Aircraft Certification Office,
Engine & Propeller Directorate, 1200 District Avenue, Burlington,
Massachusetts 01803; telephone (781) 238-7693; email
dorie.resnik@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
Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic
Issue, dated January 30, 2015, which is not incorporated by
reference, contains additional information about the subject of this
AD. For service information identified in this AD, contact Sikorsky
Aircraft Corporation, Customer Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email:
wcs_cust_service_eng.gr-sik@lmco.com. You may review this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 3200 Main Landing
Gear and 3220 Nose Landing Gear.
(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.
(i) Ultrasonic Inspection Technique No. UT 5077, Revision 0,
dated July 25, 2014.
Note 2 to paragraph (i)(2)(i): Ultrasonic Inspection Technique
No. UT 5077, Revision 0, dated July 25, 2014, is an attachment to
Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic
Issue, dated
[[Page 34841]]
January 30, 2015, which is not incorporated by reference.
(ii) Reserved.
(3) For Sikorsky service information identified in this AD,
contact Sikorsky Aircraft Corporation, Customer Service Engineering,
124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or
203-416-4299; email: wcs_cust_service_eng.gr-sik@lmco.com.
(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 June 27, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-15222 Filed 7-26-17; 8:45 am]
BILLING CODE 4910-13-P