Airworthiness Directives; Bell Helicopter Textron Canada, 38613-38615 [2015-16469]
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38613
Rules and Regulations
Federal Register
Vol. 80, No. 129
Tuesday, July 7, 2015
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0499; Directorate
Identifier 2013–SW–061–AD; Amendment
39–18198; AD 2015–13–11]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
Helicopter Textron Canada (BHTC)
Model 430 helicopters to require
inspecting the tail rotor control tube
assembly (control tube) and either
repairing or replacing the control tube.
This AD was prompted by two reports
of failure of the control tube bonded
clevis. The actions of this AD are
intended to prevent failure of a control
tube bonded clevis, which could lead to
failure of the control tube and
subsequent loss of helicopter control.
DATES: This AD is effective August 11,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 11, 2015.
ADDRESSES: 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 the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137. It is also available
on the Internet at https://
srobinson on DSK5SPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
19:51 Jul 06, 2015
Jkt 235001
www.regulations.gov in Docket No.
FAA–2014–0499.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the Transport
Canada Civil Aviation (TCCA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 2601 Meacham Blvd.,
Fort Worth, Texas 76137; telephone
(817) 222–5110; email matthew.fuller@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 30, 2014, at 79 FR 44147, 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
BHTC Model 430 Helicopters, serial
number 49001 through 49121, with
control tube part number (P/N) 430–
001–007–101 installed. The NPRM
proposed to require inspecting the
control tube and either repairing or
replacing it. The proposed requirements
were intended to prevent failure of a
control tube bonded clevis, which could
lead to failure of the control tube and
subsequent loss of helicopter control.
The NPRM was prompted by
Canadian AD No. CF–2013–30, dated
October 7, 2013, issued by TCCA, which
is the aviation authority for Canada, to
correct an unsafe condition for BHTC
Model 430 helicopters with control tube
P/N 430–001–007–101. TCCA advises of
two failures of the control tube bonded
clevis caused by cracking from control
tube oscillation. TCCA states that this
situation, if not corrected, could result
in the loss of control of the helicopter.
TCCA AD No. CF–2013–30
consequently requires a one-time
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
inspection of the control tube for
damage and contacting BHTC for
evaluation of the control tube if the
damage exceeds allowable limits. If the
tube is not damaged, the damage is
within allowable limits, or BHTC
Engineering determines the control tube
can be returned to service, TCCA AD
No. CF–2013–30 requires modifying the
tube according to BHTC’s service
information. TCCA AD No. CF–2013–30
also requires replacing control tubes, P/
N 430–001–007–101, with control tube,
P/N 430–001–007–105, no later than 12
months from the effective date of its AD.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(79 FR 44147, July 30, 2014).
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, TCCA, its
technical representative, has notified us
of the unsafe condition described in the
TCCA AD. We are issuing this AD
because we evaluated all information
provided by TCCA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Differences Between This AD and the
TCCA AD
The TCCA AD requires submitting
sketches of a control tube damaged
beyond defined limits to BHTC for
evaluation. BHTC then determines if the
control tube can be returned to service.
We make no such requirement in this
AD.
Related Service Information Under 1
CFR Part 51
Bell Helicopter Alert Service Bulletin
(ASB) No. 430–13–51, dated September
3, 2013, states that BHTC received two
reports of control tube, P/N 430–001–
007–101, failing because the clevis
failed due to fatigue caused by control
tube oscillation. ASB No. 430–13–51
specifies a one-time inspection of
control tube assembly, P/N 430–001–
007–101, to verify if the tube has
chaffing damage and indicated that a
E:\FR\FM\07JYR1.SGM
07JYR1
38614
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations
mandatory replacement would follow
when sufficient parts became available.
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 of
this AD.
Other Related Service Information
We reviewed Bell Helicopter
Technical Bulletin 430–04–35, Revision
B, dated March 20, 2009, which
recommends that control tube, P/N 430–
001–007–101, be replaced with control
tube, P/N 430–001–007–105, if damage
exists. On June 12, 2014, Bell issued
Revision A to ASB No. 430–13–51,
which set a compliance date of
September 30, 2014, to remove control
tube, P/N 430–001–007–101.
srobinson on DSK5SPTVN1PROD with RULES
Costs of Compliance
We estimate that this AD affects 5
helicopters of U.S. Registry and that
labor costs average $85 a work hour.
Based on these estimates, we expect the
following costs:
• The cost of inspecting the control
tube is minimal.
• Repairing the control tube requires
2 work-hours for a labor cost of $170.
• Replacing control tube, P/N 430–
001–007–101, with control tube, P/N
430–001–007–105, requires 3 workhours for a labor cost of $255. Parts cost
$3,974 for a total cost per helicopter of
$4,229.
According to manufacturer’s service
information, some of the costs of this
AD may be covered under warranty,
thereby reducing the cost impact on
affected individuals. We do not control
warranty coverage by the manufacturer.
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
VerDate Sep<11>2014
19:51 Jul 06, 2015
Jkt 235001
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:
■
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):
■
2015–13–11 Bell Helicopter Textron
Canada: Amendment 39–18198; Docket
No. FAA–2014–0499; Directorate
Identifier 2013–SW–061–AD.
(a) Applicability
This AD applies to Bell Helicopter Textron
Canada (BHTC) Model 430 Helicopters, serial
number 49001 through 49121, with control
tube assembly (control tube), part number (P/
N) 430–001–007–101 installed, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
fatigue failure of a tail rotor control tube
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
bonded clevis. This condition could result in
failure of the tail rotor control tube and
subsequent loss of helicopter control.
(c) Effective Date
This AD becomes effective August 11,
2015.
(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 50 hours time-in-service (TIS),
visually inspect each control tube for any
damage, for any damage to the clevis, and to
determine whether the clevis is correctly
bonded to the control tube.
(i) If a control tube and clevis have no
damage or damage within acceptable limits
and the clevis is correctly bonded to the
control tube, repair the control tube by
applying tape in accordance with the
Accomplishment Instructions, Paragraph 5,
of Bell Helicopter Alert Service Bulletin 430–
13–51, dated September 3, 2013.
(ii) If the control tube or clevis is damaged
beyond acceptable limits or if the clevis is
not correctly bonded to the control tube,
replace control tube, P/N 430–001–007–101,
with control tube, P/N 430–001–007–105.
(2) Within 250 hours TIS, replace each
control tube, P/N 430–001–007–101, with
control tube, P/N 430–001–007–105.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller,
Senior Aviation Safety Engineer, Safety
Management Group, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5110;
email matthew.fuller@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
(1) Bell Helicopter Technical Bulletin 430–
04–35, Revision B, dated March 20, 2009,
which is not incorporated by reference,
contains additional information about the
subject of this AD. For service information,
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
view this service information at FAA, Office
of the Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
No. CF–2013–30, dated October 7, 2013. You
may view the TCCA AD on the Internet at
E:\FR\FM\07JYR1.SGM
07JYR1
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations
https://www.regulations.gov in Docket No.
FAA–2014–0499.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6720, Tail Rotor Control
(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 the AD specifies otherwise.
(i) Bell Helicopter Alert Service Bulletin
430–13–51, dated September 3, 2013.
(ii) Reserved.
(3) For Bell Helicopter Textron Canada
Limited 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/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on June 24,
2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–16469 Filed 7–6–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0569; Directorate
Identifier 2014–NM–047–AD; Amendment
39–18199; AD 2015–14–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
srobinson on DSK5SPTVN1PROD with RULES
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This AD was prompted
by a report of loose bolts that are
SUMMARY:
VerDate Sep<11>2014
19:51 Jul 06, 2015
Jkt 235001
intended to secure the translating door
crank assembly to the outside handle
shaft. This AD requires a detailed
inspection for loose bolts on the aft
translating door crank assembly, and
removal and reinstallation of the bolts.
We are issuing this AD to prevent loose
bolts from falling out. If both bolts
become loose or fall out after the door
is closed and locked, the door cannot be
opened from inside or outside, which
could impede evacuation in the event of
an emergency.
DATES: This AD becomes effective
August 11, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 11, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0569; or in
person at the 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.
For service information identified in
this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; telephone 416–375–4000; fax
416–375–4539; email thd.qseries@
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–2014–
0569.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7318; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
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
DHC–8–400 series airplanes. The NPRM
published in the Federal Register on
August 15, 2014 (79 FR 48105). The
NPRM was prompted by a report of
loose bolts that are intended to secure
the translating door crank assembly to
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
38615
the outside handle shaft. The NPRM
proposed to require a detailed
inspection for loose bolts on the aft
translating door crank assembly, and
removal and reinstallation of the bolts.
We are issuing this AD to prevent loose
bolts from falling out. If both bolts
become loose or fall out after the door
is closed and locked, the door cannot be
opened from inside or outside, which
could impede evacuation in the event of
an emergency.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2014–08,
dated February 10, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
There was one in-service report where the
bolts securing the translating door crank
assembly to the outside handle shaft were
found loose. It was also found on another
translating door that sealant was missing on
these bolts. If both bolts become loose or fall
out after the door is closed and locked, the
door cannot be opened from inside or
outside.
The aft entry translating door and aft
service translating door are classified as
emergency exits. The inability to open an
emergency exit could impede evacuation in
the event of an emergency.
This [Canadian] AD mandates the
inspection of the translating door crank
assemblies for loose bolts, as well as
appropriate rectification [removal and
reinstallation of the bolts].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-05690002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
The following presents the comment
received on the NPRM (79 FR 48105,
August 15, 2014), and the FAA’s
response to the comment.
Request To Remove Certain
Requirements From the NPRM (79 FR
48105, August 15, 2014)
Horizon Air requested that the job setup and close-out procedures included in
Part A–INSPECTION, and Part B–
RECTIFICATION, of the
Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013, be
removed as requirements in the NPRM
(79 FR 48105, August 15, 2014). The
commenter noted that only the
procedures included in paragraph B.
E:\FR\FM\07JYR1.SGM
07JYR1
Agencies
[Federal Register Volume 80, Number 129 (Tuesday, July 7, 2015)]
[Rules and Regulations]
[Pages 38613-38615]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16469]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules
and Regulations
[[Page 38613]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD;
Amendment 39-18198; AD 2015-13-11]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Bell
Helicopter Textron Canada (BHTC) Model 430 helicopters to require
inspecting the tail rotor control tube assembly (control tube) and
either repairing or replacing the control tube. This AD was prompted by
two reports of failure of the control tube bonded clevis. The actions
of this AD are intended to prevent failure of a control tube bonded
clevis, which could lead to failure of the control tube and subsequent
loss of helicopter control.
DATES: This AD is effective August 11, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 11,
2015.
ADDRESSES: 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 the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137. It is also available on the Internet at https://www.regulations.gov in Docket No. FAA-2014-0499.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the Transport Canada Civil
Aviation (TCCA) AD, any incorporated-by-reference service information,
the economic evaluation, any comments received, and other information.
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 30, 2014, at 79 FR 44147, 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 BHTC Model 430
Helicopters, serial number 49001 through 49121, with control tube part
number (P/N) 430-001-007-101 installed. The NPRM proposed to require
inspecting the control tube and either repairing or replacing it. The
proposed requirements were intended to prevent failure of a control
tube bonded clevis, which could lead to failure of the control tube and
subsequent loss of helicopter control.
The NPRM was prompted by Canadian AD No. CF-2013-30, dated October
7, 2013, issued by TCCA, which is the aviation authority for Canada, to
correct an unsafe condition for BHTC Model 430 helicopters with control
tube P/N 430-001-007-101. TCCA advises of two failures of the control
tube bonded clevis caused by cracking from control tube oscillation.
TCCA states that this situation, if not corrected, could result in the
loss of control of the helicopter. TCCA AD No. CF-2013-30 consequently
requires a one-time inspection of the control tube for damage and
contacting BHTC for evaluation of the control tube if the damage
exceeds allowable limits. If the tube is not damaged, the damage is
within allowable limits, or BHTC Engineering determines the control
tube can be returned to service, TCCA AD No. CF-2013-30 requires
modifying the tube according to BHTC's service information. TCCA AD No.
CF-2013-30 also requires replacing control tubes, P/N 430-001-007-101,
with control tube, P/N 430-001-007-105, no later than 12 months from
the effective date of its AD.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (79 FR 44147, July 30,
2014).
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, TCCA, its technical
representative, has notified us of the unsafe condition described in
the TCCA AD. We are issuing this AD because we evaluated all
information provided by TCCA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed.
Differences Between This AD and the TCCA AD
The TCCA AD requires submitting sketches of a control tube damaged
beyond defined limits to BHTC for evaluation. BHTC then determines if
the control tube can be returned to service. We make no such
requirement in this AD.
Related Service Information Under 1 CFR Part 51
Bell Helicopter Alert Service Bulletin (ASB) No. 430-13-51, dated
September 3, 2013, states that BHTC received two reports of control
tube, P/N 430-001-007-101, failing because the clevis failed due to
fatigue caused by control tube oscillation. ASB No. 430-13-51 specifies
a one-time inspection of control tube assembly, P/N 430-001-007-101, to
verify if the tube has chaffing damage and indicated that a
[[Page 38614]]
mandatory replacement would follow when sufficient parts became
available. 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 of this
AD.
Other Related Service Information
We reviewed Bell Helicopter Technical Bulletin 430-04-35, Revision
B, dated March 20, 2009, which recommends that control tube, P/N 430-
001-007-101, be replaced with control tube, P/N 430-001-007-105, if
damage exists. On June 12, 2014, Bell issued Revision A to ASB No. 430-
13-51, which set a compliance date of September 30, 2014, to remove
control tube, P/N 430-001-007-101.
Costs of Compliance
We estimate that this AD affects 5 helicopters of U.S. Registry and
that labor costs average $85 a work hour. Based on these estimates, we
expect the following costs:
The cost of inspecting the control tube is minimal.
Repairing the control tube requires 2 work-hours for a
labor cost of $170.
Replacing control tube, P/N 430-001-007-101, with control
tube, P/N 430-001-007-105, requires 3 work-hours for a labor cost of
$255. Parts cost $3,974 for a total cost per helicopter of $4,229.
According to manufacturer's service information, some of the costs
of this AD may be covered under warranty, thereby reducing the cost
impact on affected individuals. We do not control warranty coverage by
the manufacturer. 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 helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2015-13-11 Bell Helicopter Textron Canada: Amendment 39-18198;
Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD.
(a) Applicability
This AD applies to Bell Helicopter Textron Canada (BHTC) Model
430 Helicopters, serial number 49001 through 49121, with control
tube assembly (control tube), part number (P/N) 430-001-007-101
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue failure of a
tail rotor control tube bonded clevis. This condition could result
in failure of the tail rotor control tube and subsequent loss of
helicopter control.
(c) Effective Date
This AD becomes effective August 11, 2015.
(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 50 hours time-in-service (TIS), visually inspect each
control tube for any damage, for any damage to the clevis, and to
determine whether the clevis is correctly bonded to the control
tube.
(i) If a control tube and clevis have no damage or damage within
acceptable limits and the clevis is correctly bonded to the control
tube, repair the control tube by applying tape in accordance with
the Accomplishment Instructions, Paragraph 5, of Bell Helicopter
Alert Service Bulletin 430-13-51, dated September 3, 2013.
(ii) If the control tube or clevis is damaged beyond acceptable
limits or if the clevis is not correctly bonded to the control tube,
replace control tube, P/N 430-001-007-101, with control tube, P/N
430-001-007-105.
(2) Within 250 hours TIS, replace each control tube, P/N 430-
001-007-101, with control tube, P/N 430-001-007-105.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Group, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5110; email matthew.fuller@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
(1) Bell Helicopter Technical Bulletin 430-04-35, Revision B,
dated March 20, 2009, which is not incorporated by reference,
contains additional information about the subject of this AD. For
service information, 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 view this service information
at FAA, Office of the Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in Transport Canada
Civil Aviation (TCCA) AD No. CF-2013-30, dated October 7, 2013. You
may view the TCCA AD on the Internet at
[[Page 38615]]
https://www.regulations.gov in Docket No. FAA-2014-0499.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor
Control
(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 the AD specifies otherwise.
(i) Bell Helicopter Alert Service Bulletin 430-13-51, dated
September 3, 2013.
(ii) Reserved.
(3) For Bell Helicopter Textron Canada Limited 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/.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. 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 24, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-16469 Filed 7-6-15; 8:45 am]
BILLING CODE 4910-13-P