Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters, 39004-39007 [2018-16637]
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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
information collection. The NCUA may
not conduct or sponsor, and the
respondent is not required to respond
to, an information collection unless it
displays a currently valid Office of
Management and Budget (OMB) control
number.
The proposed changes to part 702
would increase the asset size of credit
unions identified as complex from
greater than $100 million to greater than
$500 million. This change would reduce
the number of credit unions who must
comply with recordkeeping
requirements prescribed by § 702.101(b).
Therefore, the burden cleared under
OMB number 3133–0191 will be revised
to reflect the reduction in the number of
respondents.50
Title of Information Collection:
Prompt Corrective Action—Risk-Based
Capital.
OMB Control Number: 3133–0191.
Affected Public: Private Sector: Notfor-profit institutions—Complex Credit
Unions.
Estimated Number of Respondents:
531.
Estimated Number of Responses per
Respondent: 1.
Estimated Hours per Response: 40.
Estimated Total Annual Burden
Hours: 21,240.
By exempting credit unions with
assets between $100 million and $500
million, the NCUA estimates that the
burden under this proposed rule would
be 41,040 fewer hours.
The Board invites comment on (a)
whether the collections of information
are necessary for the proper
performance of the agency’s function,
including practical utility; (b) the
accuracy of estimates of the burden of
the information collections, including
the validity of the methodology and
assumptions used; (c) ways to enhance
the quality, utility, and clarity of the
information being collected, and (d)
ways to minimize the burden of the
information collection on respondents,
including through the use of automated
collection techniques or other forms of
information technology.
All comments are a matter of public
record. Comments regarding the
information collection requirements of
this rule should be sent to (1) Dawn
Wolfgang, NCUA PRA Clearance
Officer, National Credit Union
Administration, 1775 Duke Street, Suite
5080, Alexandria, Virginia 22314, or Fax
No. 703–519–8572, or Email at
PRAcomments@ncua.gov and the (2)
Office of Information and Regulatory
50 Proposed revisions to OMB control number
3133–0191 have been submitted to OMB for
approval in accordance with 5 CFR 1320.11.
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Affairs, Office of Management and
Budget, Attention: Desk Officer for
NCUA, New Executive Office Building,
Room 10235, Washington, DC 20503, or
email at
OIRA_Submission,@OMB.EOP.gov.
Submission of comments. The NCUA
considers comments by the public on
this proposed collection of information
in:
• Evaluating whether the proposed
collection of information is necessary
for the proper performance of the
functions of the NCUA, including
whether the information will have a
practical use;
• Evaluating the accuracy of the
NCUA’s estimate of the burden of the
proposed collection of information,
including the validity of the
methodology and assumptions used;
• Enhancing the quality, usefulness,
and clarity of the information to be
collected; and
• Minimizing the burden of collection
of information on those who are to
respond, including through the use of
appropriate automated, electronic,
mechanical, or other technological
collection techniques or other forms of
information technology; e.g., permitting
electronic submission of responses.
Executive Order 13132 encourages
independent regulatory agencies to
consider the impact of their actions on
state and local interests. The NCUA, an
independent regulatory agency as
defined in 44 U.S.C. 3502(5), voluntarily
complies with the principles of the
executive order to adhere to
fundamental federalism principles. This
proposed rule reduces the number of
federally insured natural-person credit
unions, including federally insured,
state-chartered natural-person credit
unions that would be subject to the 2015
Final Rule. It may have, to some degree,
a 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. It does not,
however, rise to the level of material
impact for purposed of Executive Order
13132.
Assessment of Federal Regulations and
Policies on Families
The NCUA has determined that this
proposed rule will not affect family
well-being within the meaning of
section 654 of the Treasury and General
Government Appropriations Act, 1999,
Public Law 105–277, 112 Stat. 2681
(1998).
Frm 00023
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Sfmt 4702
Credit unions, Reporting and
recordkeeping requirements.
By the National Credit Union
Administration Board on August 2, 2018.
Gerard Poliquin,
Secretary of the Board.
For the reasons discussed above, the
Board proposes to further amend 12
CFR part 702, as amended in a final rule
at 80 FR 66625 (Oct. 29, 2015), effective
January 1, 2019, as follows:
PART 702—CAPITAL ADEQUACY
1. The authority citation for part 702
continues to read as follows:
■
Authority: 12 U.S.C. 1766(a), 1790d.
§ 702.103
[Amended]
2. Amend § 702.103 by removing the
words ‘‘one hundred million dollars
($100,000,000)’’ and add in their place
‘‘five hundred million dollars
($500,000,000).’’
■
[FR Doc. 2018–16888 Filed 8–7–18; 8:45 am]
BILLING CODE 7535–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Executive Order 13132
PO 00000
List of Subjects in 12 CFR Part 702
14 CFR Part 39
[Docket No. FAA–2018–0722; Product
Identifier 2017–SW–104–AD
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Limited
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2015–22–
02 for Bell Helicopter Textron Canada
Limited (Bell) Model 429 helicopters.
AD 2015–22–02 requires inspecting the
tail rotor (TR) pitch link assemblies.
This proposed AD would retain the
inspections of AD 2015–22–02 and
would require replacing certain pitch
link bearings. Since we issued AD
2015–22–02, Bell has introduced a new
design bearing. The actions of this
proposed AD are intended to prevent an
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by October 9, 2018.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
• 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–2018–
0722; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the Transport Canada AD, the
economic evaluation, any comments
received, and other information. The
street address for Docket Operations
(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 Bell Helicopter
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4;
telephone (450) 437–2862 or (800) 363–
8023; fax (450) 433–0272; or at https://
www.bellcustomer.com/files/. 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.
FOR FURTHER INFORMATION CONTACT:
David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
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 might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
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commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit 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 proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
new bearings. We propose to issue this
AD to make similar changes.
Discussion
Related Service Information
Bell has issued Alert Service Bulletin
No. 429–15–16, Revision B, dated June
15, 2016. This service information
contains procedures for repetitively
inspecting the TR pitch link assembly
until it is upgraded by replacing the TR
pitch link bearings.
We issued AD 2015–22–02,
Amendment 39–18306 (80 FR 65618,
October 27, 2015) (AD 2015–22–02), for
Bell Model 429 helicopters with a TR
pitch link assembly part number (P/N)
429–112–101 or 429–112–103 installed.
AD 2015–22–02 requires repetitively
inspecting each inboard and outboard
TR pitch link assembly for axial or
radial bearing play every 50 hours timein-service (TIS), performing a
dimensional inspection of the TR pitch
link if there is axial or radial bearing
play, and replacing the TR pitch link
before further flight if there is any wear
beyond allowable limits. AD 2015–22–
02 was prompted by Emergency AD No.
CF–2015–16, dated July 2, 2015, and
Emergency AD No. CF–2015–16R1,
dated August 6, 2015, issued by
Transport Canada, to correct an unsafe
condition for Bell Model 429
helicopters. Transport Canada advised
of several occasions where the TR pitch
link spherical bearings experienced
early and accelerated wear.
Actions Since AD 2015–22–02 Was
Issued
Since we issued AD 2015–22–02,
Transport Canada has issued AD No.
CF–2015–16R2, dated April 17, 2017,
which supersedes AD CF–2015–16R1.
According to Transport Canada, Bell has
reported that the TR pitch link assembly
can be rotated during the 50-hour
inspections to extend the serviceability
life of the bearings. Transport Canada
AD No. CF–2015–16R2 requires
modified inspection procedures for the
spherical bearings and requires
replacing the TR pitch link bearings (or
the TR pitch link assembly) with
spherical bearings manufactured after
January 12, 2015. Transport Canada AD
No. CF–2015–16R2 also requires reidentifying TR pitch link assemblies
with a different P/N after installing the
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Sfmt 4702
FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, Transport
Canada, its technical representative, has
notified us of the unsafe condition
described in the Transport Canada AD.
We are proposing this AD because we
evaluated all information provided by
Transport Canada and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
AD Requirements
This proposed AD would require
performing a dimensional inspection of
the spherical bearings for axial and
radial play and inspecting the TR pitch
link assembly sealant for pin holes,
voids, and excessive thickness. These
inspections would be required within
50 hours TIS and thereafter at intervals
not exceeding 50 hours TIS.
This proposed AD would also require
replacing any spherical bearing
manufactured before January 13, 2015,
that has exceeded 250 hours TIS or that
has an unknown number of hours TIS,
and re-identifying the P/N of the TR
pitch link assembly.
Differences Between This Proposed AD
and the Transport Canada AD
The Transport Canada AD requires
the bearing inspection within 10 hours
TIS or before exceeding 60 hours TIS
since new, whichever occurs later. This
proposed AD would require the bearing
inspection within 50 hours TIS. The
Transport Canada AD also requires
replacing certain bearings within 200
hours TIS after the initial bearing
inspection or within 250 hours TIS
since new, whichever occurs first. This
proposed AD would require replacing
the bearing within 200 hours of the
initial inspection or at the next 50 hour
TIS inspection if the hours TIS of a
pitch link assembly exceed 250 hours
TIS or are unknown.
Interim Action
We consider this proposed AD to be
an interim action. If final action is later
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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
identified, we might consider further
rulemaking then.
Costs of Compliance
We estimate that this proposed AD
would affect 85 helicopters of U.S.
Registry. We estimate that operators
may incur the following costs in order
to comply with this proposed AD. At an
average labor rate of $85 per hour,
inspecting the TR pitch link assemblies
would require 2 work-hours for a cost of
$170 per helicopter and $14,450 for the
U.S. fleet per inspection cycle.
Replacing both spherical bearings in
each TR pitch link assembly would
require 3 work-hours, and required parts
would cost $3,088, for a cost of $3,343
per helicopter and $284,155 for the U.S.
fleet.
According to Bell’s service
information some of the costs of this
proposed AD may be covered under
warranty, thereby reducing the cost
impact on affected individuals. We do
not control warranty coverage by Bell.
Accordingly, we have included all costs
in our cost estimate.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
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.
Regulatory Findings
We determined that this proposed AD
will not have federalism implications
under Executive Order 13132. This
proposed 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 proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–22–02, Amendment 39–18306 (80
FR 65618, October 27, 2015), and
adding the following new AD:
■
Bell Helicopter Textron Canada Limited:
Docket No. FAA–2018–0722; Product
Identifier 2017–SW–104–AD.
(a) Applicability
This AD applies to Model 429 helicopters
with a pitch link assembly part number
(P/N) 429–012–112–101, 429–012–112–103,
429–012–112–101FM, or 429–012–112–
103FM installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
worn pitch link. This condition, if not
corrected, could result in pitch link failure
and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD replaces AD 2015–22–02,
Amendment 39–18306 (80 FR 65618, October
27, 2015).
(d) Comments Due Date
We must receive comments by October 9,
2018.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
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Sfmt 4702
(f) Required Actions
(1) Within 50 hours time-in-service (TIS)
and thereafter at intervals not to exceed 50
hours TIS:
(i) Perform a dimensional inspection of
each inboard and outboard pitch link
assembly for axial and radial bearing play.
With a 10X or higher power magnifying glass,
inspect the bearing liner for a crack,
deterioration of the liner, and extrusion of
the liner from the plane. If there is axial or
radial play that exceeds allowable limits, or
if there is a crack, deterioration of the liner,
or extrusion of the liner, before further flight,
replace the bearing.
(ii) Inspect the pitch link assembly sealant
for pin holes and voids and to determine if
the sealant thickness is 0.025 inch (0.64 mm)
or less, extends over the roll staked lip by
0.030 inch (0.76 mm) or more, and is clear
of the bearing ball. If there is a pin hole or
void, or if the sealant exceeds 0.026 inch
(0.66 mm), does not extend over the roll
staked lip by 0.030 inch (0.76 mm) or more,
or is not clear of the bearing ball, before
further flight, replace the bearing.
(2) For pitch link assembly part number
(P/N) 429–012–112–101, 429–012–112–103,
429–012–112–101FM, and 429–012–112–
103FM, within 200 hours TIS following the
initial inspection required by paragraph (f)(1)
of this AD, or if the hours TIS of a pitch link
assembly exceed 250 hours TIS or are
unknown, at the next 50 hour TIS inspection
required by paragraph (f)(1) of this AD:
(i) Replace each bearing P/N 429–312–107–
103 with a date of manufacture before
January 13, 2015, with a bearing P/N 429–
312–107–103 that was manufactured on or
after January 13, 2015.
(ii) Using a white permanent fine point
marker or equivalent, re-identify the pitch
link assembly:
(A) Re-identify P/N 429–012–112–101 and
429–012–112–101FM as 429–012–112–
111FM.
(B) Re-identify P/N 429–012–112–103 and
429–012–112–103FM as 429–012–112–
113FM.
(iii) Apply a coating of DEVCON 2–TON
(C–298) or equivalent over the new P/N.
(g) Special Flight Permits
Special flight permits are prohibited.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, 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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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
(i) Additional Information
(1) Bell Alert Service Bulletin No. 429–15–
16, Revision B, dated June 15, 2016, which
is not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4; telephone (450)
437–2862 or (800) 363–8023; fax (450) 433–
0272; or at https://www.bellcustomer.com/
files/. 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
Transport Canada AD No. CF–2015–16R2,
dated April 17, 2017. You may view the
Transport Canada AD on the internet at
https://www.regulations.gov in the AD Docket.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6720 Tail Rotor Control System.
Issued in Fort Worth, Texas, on July 23,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–16637 Filed 8–7–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0669; Product
Identifier 2017–SW–041–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–25–
19 for Airbus Helicopters (previously
Eurocopter France) Model AS350B3 and
EC130B4 helicopters. AD 2016–25–19
requires inspecting the pilot’s and copilot’s throttle twist for proper
operation. This proposed AD would
retain the requirements of AD 2016–25–
19 and add certain model helicopters to
the applicability. The actions of this
proposed AD are intended to address
the unsafe condition on these
helicopters.
DATES: We must receive comments on
this proposed AD by October 9, 2018.
ADDRESSES: You may send comments by
any of the following methods:
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SUMMARY:
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• 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–2018–
0669; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the European Aviation Safety
Agency (EASA) AD, the economic
evaluation, any comments received and
other information. The street address for
Docket Operations (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 proposed rule, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
may review service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
george.schwab@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
PO 00000
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39007
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
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 proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Discussion
We issued AD 2016–25–19,
Amendment 39–18745 (81 FR 95854,
December 29, 2016) (AD 2016–25–19),
for Airbus Helicopters Model AS350B3
and EC130B4 helicopters with the
ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine
Control (FADEC) and with new twist
grip modification (MOD) 073254 (for the
Model AS350B3 helicopter) or MOD
073773 (for the Model EC130B4
helicopter). AD 2016–25–19 requires
repetitively inspecting the wiring,
performing an insulation test, inspecting
the pilot and copilot throttle twist grip
controls, and testing the pilot and
copilot throttle twist grip controls for
proper functioning. AD 2016–25–19 was
prompted by AD No. 2013–0191–E,
dated August 22, 2013 (EASA AD 2013–
0191–E), issued by EASA, which is the
Technical Agent for the Member States
of the European Union. EASA advised
that the switches in the engine ‘‘IDLE’’
or ‘‘FLIGHT’’ control system could be
affected by the corrosive effects of a saltladen atmosphere, which could lead to
engine power loss. EASA AD 2013–
0191–E required repetitive inspections
for corrosion, application of corrosion
protection on the switches, and testing
of the insulation and switches of the
engine idle and flight control system.
The actions required in AD 2016–25–19
are intended to prevent unintended
touchdown to the ground at a flight-idle
power setting during a practice
autorotation, damage to the helicopter,
and injury to occupants.
Actions Since AD 2016–25–19 Was
Issued
Since we issued AD 2016–25–19,
EASA issued AD No. 2017–0052, dated
March 24, 2017, which superseded
EASA AD No. 2013–0191–E, dated
August 22, 2013. EASA advised that
Airbus Helicopters had added
E:\FR\FM\08AUP1.SGM
08AUP1
Agencies
[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Proposed Rules]
[Pages 39004-39007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16637]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0722; Product Identifier 2017-SW-104-AD
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Limited
Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2015-22-
02 for Bell Helicopter Textron Canada Limited (Bell) Model 429
helicopters. AD 2015-22-02 requires inspecting the tail rotor (TR)
pitch link assemblies. This proposed AD would retain the inspections of
AD 2015-22-02 and would require replacing certain pitch link bearings.
Since we issued AD 2015-22-02, Bell has introduced a new design
bearing. The actions of this proposed AD are intended to prevent an
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by October 9, 2018.
ADDRESSES: You may send comments by any of the following methods:
[[Page 39005]]
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-2018-
0722; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this proposed AD, the Transport Canada AD, the economic evaluation, any
comments received, and other information. The street address for Docket
Operations (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 Bell
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450)
433-0272; or at https://www.bellcustomer.com/files/. 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.
FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
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 proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
We issued AD 2015-22-02, Amendment 39-18306 (80 FR 65618, October
27, 2015) (AD 2015-22-02), for Bell Model 429 helicopters with a TR
pitch link assembly part number (P/N) 429-112-101 or 429-112-103
installed. AD 2015-22-02 requires repetitively inspecting each inboard
and outboard TR pitch link assembly for axial or radial bearing play
every 50 hours time-in-service (TIS), performing a dimensional
inspection of the TR pitch link if there is axial or radial bearing
play, and replacing the TR pitch link before further flight if there is
any wear beyond allowable limits. AD 2015-22-02 was prompted by
Emergency AD No. CF-2015-16, dated July 2, 2015, and Emergency AD No.
CF-2015-16R1, dated August 6, 2015, issued by Transport Canada, to
correct an unsafe condition for Bell Model 429 helicopters. Transport
Canada advised of several occasions where the TR pitch link spherical
bearings experienced early and accelerated wear.
Actions Since AD 2015-22-02 Was Issued
Since we issued AD 2015-22-02, Transport Canada has issued AD No.
CF-2015-16R2, dated April 17, 2017, which supersedes AD CF-2015-16R1.
According to Transport Canada, Bell has reported that the TR pitch link
assembly can be rotated during the 50-hour inspections to extend the
serviceability life of the bearings. Transport Canada AD No. CF-2015-
16R2 requires modified inspection procedures for the spherical bearings
and requires replacing the TR pitch link bearings (or the TR pitch link
assembly) with spherical bearings manufactured after January 12, 2015.
Transport Canada AD No. CF-2015-16R2 also requires re-identifying TR
pitch link assemblies with a different P/N after installing the new
bearings. We propose to issue this AD to make similar changes.
FAA's Determination
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
our bilateral agreement with Canada, Transport Canada, its technical
representative, has notified us of the unsafe condition described in
the Transport Canada AD. We are proposing this AD because we evaluated
all information provided by Transport Canada and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design.
Related Service Information
Bell has issued Alert Service Bulletin No. 429-15-16, Revision B,
dated June 15, 2016. This service information contains procedures for
repetitively inspecting the TR pitch link assembly until it is upgraded
by replacing the TR pitch link bearings.
AD Requirements
This proposed AD would require performing a dimensional inspection
of the spherical bearings for axial and radial play and inspecting the
TR pitch link assembly sealant for pin holes, voids, and excessive
thickness. These inspections would be required within 50 hours TIS and
thereafter at intervals not exceeding 50 hours TIS.
This proposed AD would also require replacing any spherical bearing
manufactured before January 13, 2015, that has exceeded 250 hours TIS
or that has an unknown number of hours TIS, and re-identifying the P/N
of the TR pitch link assembly.
Differences Between This Proposed AD and the Transport Canada AD
The Transport Canada AD requires the bearing inspection within 10
hours TIS or before exceeding 60 hours TIS since new, whichever occurs
later. This proposed AD would require the bearing inspection within 50
hours TIS. The Transport Canada AD also requires replacing certain
bearings within 200 hours TIS after the initial bearing inspection or
within 250 hours TIS since new, whichever occurs first. This proposed
AD would require replacing the bearing within 200 hours of the initial
inspection or at the next 50 hour TIS inspection if the hours TIS of a
pitch link assembly exceed 250 hours TIS or are unknown.
Interim Action
We consider this proposed AD to be an interim action. If final
action is later
[[Page 39006]]
identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this proposed AD would affect 85 helicopters of
U.S. Registry. We estimate that operators may incur the following costs
in order to comply with this proposed AD. At an average labor rate of
$85 per hour, inspecting the TR pitch link assemblies would require 2
work-hours for a cost of $170 per helicopter and $14,450 for the U.S.
fleet per inspection cycle. Replacing both spherical bearings in each
TR pitch link assembly would require 3 work-hours, and required parts
would cost $3,088, for a cost of $3,343 per helicopter and $284,155 for
the U.S. fleet.
According to Bell's service information some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected individuals. We do not control warranty coverage by
Bell. Accordingly, we have included all costs in our cost estimate.
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.
Regulatory Findings
We determined that this proposed AD will not have federalism
implications under Executive Order 13132. This proposed 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 proposed regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-22-02, Amendment 39-18306 (80 FR 65618, October 27, 2015), and
adding the following new AD:
Bell Helicopter Textron Canada Limited: Docket No. FAA-2018-0722;
Product Identifier 2017-SW-104-AD.
(a) Applicability
This AD applies to Model 429 helicopters with a pitch link
assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-
012-112-101FM, or 429-012-112-103FM installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a worn pitch link. This
condition, if not corrected, could result in pitch link failure and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD replaces AD 2015-22-02, Amendment 39-18306 (80 FR 65618,
October 27, 2015).
(d) Comments Due Date
We must receive comments by October 9, 2018.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Within 50 hours time-in-service (TIS) and thereafter at
intervals not to exceed 50 hours TIS:
(i) Perform a dimensional inspection of each inboard and
outboard pitch link assembly for axial and radial bearing play. With
a 10X or higher power magnifying glass, inspect the bearing liner
for a crack, deterioration of the liner, and extrusion of the liner
from the plane. If there is axial or radial play that exceeds
allowable limits, or if there is a crack, deterioration of the
liner, or extrusion of the liner, before further flight, replace the
bearing.
(ii) Inspect the pitch link assembly sealant for pin holes and
voids and to determine if the sealant thickness is 0.025 inch (0.64
mm) or less, extends over the roll staked lip by 0.030 inch (0.76
mm) or more, and is clear of the bearing ball. If there is a pin
hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does
not extend over the roll staked lip by 0.030 inch (0.76 mm) or more,
or is not clear of the bearing ball, before further flight, replace
the bearing.
(2) For pitch link assembly part number (P/N) 429-012-112-101,
429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within
200 hours TIS following the initial inspection required by paragraph
(f)(1) of this AD, or if the hours TIS of a pitch link assembly
exceed 250 hours TIS or are unknown, at the next 50 hour TIS
inspection required by paragraph (f)(1) of this AD:
(i) Replace each bearing P/N 429-312-107-103 with a date of
manufacture before January 13, 2015, with a bearing P/N 429-312-107-
103 that was manufactured on or after January 13, 2015.
(ii) Using a white permanent fine point marker or equivalent,
re-identify the pitch link assembly:
(A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as
429-012-112-111FM.
(B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as
429-012-112-113FM.
(iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over
the new P/N.
(g) Special Flight Permits
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
David Hatfield, Aviation Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, 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.
[[Page 39007]]
(i) Additional Information
(1) Bell Alert Service Bulletin No. 429-15-16, Revision B, dated
June 15, 2016, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4;
telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or
at https://www.bellcustomer.com/files/. 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 Transport Canada AD
No. CF-2015-16R2, dated April 17, 2017. You may view the Transport
Canada AD on the internet at https://www.regulations.gov in the AD
Docket.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor
Control System.
Issued in Fort Worth, Texas, on July 23, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-16637 Filed 8-7-18; 8:45 am]
BILLING CODE 4910-13-P