Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Helicopters, 65178-65180 [2013-25310]
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65178
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations
wreier-aviles on DSK5TPTVN1PROD with RULES
(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: Within 6,000 flight
hours after the effective date of this AD, but
not to exceed 15,600 total flight hours,
rework the bellcrank, or replace the bellcrank
with a new bellcrank or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.218
inch, but is less than or equal to 0.248 inch:
Within 6,000 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch, but is less than or equal to 0.278 inch:
Within 1,200 flight hours after doing the
measurement/inspection required by
paragraph (h) of this AD, replace the
bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having
part number 82710297–101 installed, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, Revision A, dated February 22,
2012.
(4) If any cracking is found, or if any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
with a new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(i) Actions for Certain Other Model DHC–8–
400 Series Airplanes
For Model DHC–8–400, –401, and –402
airplanes that have accumulated more than
15,000 total flight hours as of the effective
date of this AD: Within 600 flight hours after
the effective date of this AD, measure the
edge-to-edge length of the clevis holes of
each bellcrank, and inspect each bellcrank
for cracking using liquid penetrant or eddy
current inspection method; in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: Within 1,200 flight
hours after the effective date of this AD,
rework the bellcrank, or replace the bellcrank
with a new bellcrank or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than
0.218, inch but is less than or equal to 0.248
inch: Within 6,000 flight hours after the
effective date of this AD, replace the
VerDate Mar<15>2010
15:19 Oct 30, 2013
Jkt 232001
bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having
part number 82710297–101 installed, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, Revision A, dated February 22,
2012.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch, but is less than or equal to 0.278 inch:
Within 1,200 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(4) If any cracking is found, or any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
with a new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(j) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7300; fax (516)
794–5531. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2011–32, dated
August 15, 2011, for related information. The
MCAI can be found in the AD docket on the
PO 00000
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Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2012-1311-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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) Bombardier Service Bulletin 8–27–111,
dated June 15, 2011.
(ii) Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(3) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
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.
(4) You may review copies of the 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.
(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 Renton, Washington, on
September 30, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25305 Filed 10–30–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0526; Directorate
Identifier 2008–SW–14–AD; Amendment
39–17633; AD 2013–22–01]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
Model 206L–4 and 407 helicopters. This
AD requires replacing or reworking
certain aft bearing caps. This AD was
SUMMARY:
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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations
prompted by the manufacture of certain
freewheel aft bearing caps without a
lubrication channel to allow oil flow
into the aft bearing support assembly.
The actions of this AD are intended to
prevent failure of the freewheel unit and
subsequent loss of control of the
helicopter.
DATES: This AD is effective December 5,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of December 5, 2013.
ADDRESSES: For service information
identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, Texas 76101, telephone
(817) 280–3391, fax (817) 280–6466.
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.
wreier-aviles on DSK5TPTVN1PROD with RULES
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: Eric
Haight, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Regulations and
Policy Group, Fort Worth, Texas 76137,
telephone (817) 222–5110, email:
eric.haight@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 20, 2013, at 78 FR 37158, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
add an AD that would apply to Bell
Model 206L–4 and 407 helicopters. The
NPRM proposed to require, within 50
hours time-in-service (TIS), removing
and disassembling the freewheel
assembly, replacing the sprag, retainer,
and the aft seal, and visually inspecting
the remaining freewheel part details for
a missing channel. Also, the NPRM
proposed to require, if the channel is
missing, before further flight, replacing
VerDate Mar<15>2010
15:19 Oct 30, 2013
Jkt 232001
the cap assembly with an airworthy cap
or reworking and reidentifying the
existing cap by using a vibrating stylus
to add the letter ‘‘R’’ to the serial
number of the reworked cap. The
proposed actions were prompted by the
manufacture of certain freewheel aft
bearing caps without a lubrication
channel to allow oil flow into the aft
bearing support assembly. The proposed
requirements were intended to prevent
failure of the freewheel unit and
subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
CF–2004–17R1, dated February 11, 2005
(AD No. CF–2004–17R1), issued by
TCAA, which is the aviation authority
for Canada. AD No. CF–2004–17R1
requires replacing or reworking
freewheel assemblies on the Bell Model
206L–4 and 407 helicopters. TCAA
advises of a manufacturing oversight
where a lubrication channel was not
machined into the aft bearing cap of
some freewheel units to allow oil flow
into the aft bearing support assembly.
TCAA states that lack of lubrication may
adversely affect the durability and
potentially the function of the freewheel
unit.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (78 FR 37158, June 20, 2013).
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, TCAA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are issuing this AD because we
evaluated all information provided by
TCAA 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
TCAA AD
This AD differs from the TCAA AD as
follows:
• We do not use a calendar time,
which has already passed.
• We require all affected helicopters
to comply within 50 hours TIS; the
TCAA AD has different compliance
times as stipulated by the calculated
average engine start cycle count
identified in the applicable alert service
bulletin (ASB), and a 300-hour TIS
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Fmt 4700
Sfmt 4700
65179
terminating action for modifying all
affected helicopters.
• We do not require referencing
compliance with the ASBs as does the
TCAA AD, and we do not require you
to provide an affected cap for rework to
Bell Tennessee nor require the original
cap to be reworked by Bell Tennessee.
• We do not require any action on
‘‘spare’’ parts not installed on a
helicopter but would require, before
installing any replacement bearing
support assembly, ensuring that the
rework has been done.
Related Service Information
Bell has issued ASB No. 206L–04–129
for the Model 206L–4 and ASB No. 407–
04–66 for the Model 407, both Revision
A, and both dated December 1, 2004,
which specify identifying the affected
freewheel aft bearing caps. The ASBs
provide separate procedures, depending
on whether helicopters are ‘‘not
exclusively used for training’’ or
‘‘exclusively used for training,’’ for
replacing or reworking the freewheel
cap assembly and replacing the output
shaft, part number (P/N) 406–040–517–
101, and sprag and retainer, P/N 406–
040–580–103. TCCA classified these
ASBs as mandatory and issued AD No.
CF–2004–17R to ensure the continued
airworthiness of these helicopters.
Costs of Compliance
We estimate there are 212 Model
206L–4 helicopters and 540 Model 407
helicopters of U.S. registry; however, we
estimate that only 80 helicopters are
affected by this AD. We estimate that
operators may incur the following costs
in order to comply with this AD: It will
take about 16 work hours to replace the
freewheel unit for all the affected parts
at an average labor rate of $85 per work
hour. Required parts will cost about
$21,600 per helicopter. Based on these
figures, we estimate the total cost per
helicopter will be $22,900, and the total
cost of the AD on U.S. operators will be
$1,836,800.
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
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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
helicopters identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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):
wreier-aviles on DSK5TPTVN1PROD with RULES
■
2013–22–01 Bell Helicopter Textron
Canada: Amendment 39–17633; Docket
No. FAA–2013–0526; Directorate
Identifier 2008–SW–14–AD.
(a) Applicability
This AD applies to Model 206L–4 and 407
helicopters, with a freewheel aft bearing cap
(cap), part number (P/N) 406–040–509–101,
with a serial number with a prefix of ‘‘A-’’
VerDate Mar<15>2010
15:19 Oct 30, 2013
Jkt 232001
and Nos. 1833 through 1912, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
certain caps being manufactured without a
lubrication channel to allow oil flow into the
aft bearing support assembly, which could
result in failure of the freewheel unit and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 5,
2013.
(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
Within 50 hours time-in-service (TIS):
(1) Remove and disassemble each
freewheel assembly.
(2) Replace the sprag and retainer (item 7),
the output shaft (item 10), and the aft seal
(item 3), as depicted in Figure 2 of Bell Alert
Service Bulletin (ASB) No. 206L–04–129 for
the Model 206L–4 and ASB No. 407–04–66
for the Model 407, both Revision A, and both
dated December 1, 2004.
(3) Visually inspect the remaining
freewheel part details for a missing channel.
(4) If the channel is missing, replace or
rework the cap assembly by following the
instructions depicted in Figure 3 of ASB
206L–04–129 or ASB 407 04–66, as
applicable for your model helicopter. Using
a vibrating stylus, mark the letter ‘‘R’’ at the
end of the serial number on the cap
assembly.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Eric Haight,
Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Regulations and Policy Group,
Fort Worth, Texas 76137, telephone (817)
222–5110, email: eric.haight@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
The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
No. CF–2004–17R1, dated February 11, 2005.
You may view the TCCA AD at https://
www.regulations.gov in Docket No. FAA–
2013–0526.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6300: Main Rotor Drive System.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
PO 00000
Frm 00036
Fmt 4700
Sfmt 4700
(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 Alert Service Bulletin (ASB) No.
206L–04–129, Revision A, dated December 1,
2004.
(ii) Bell ASB No. 407–04–66, Revision A,
dated December 1, 2004.
(3) For Bell service information identified
in this AD, contact Bell Helicopter Textron,
Inc., P.O. Box 482, Fort Worth, Texas 76101,
telephone (817) 280–3391, fax (817) 280–
6466.
(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 October 1,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–25310 Filed 10–30–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0401; Directorate
Identifier 2012–SW–047–AD; Amendment
39–17606; AD 2013–19–24]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc., Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2003–08–
51 for MD Helicopters, Inc. (MDHI),
Model 369A, 369D, 369E, 369H, 369HE,
369HM, 369HS, 369F and 369FF
helicopters with certain MDHI or
Helicopter Technology Company (HTC)
tail rotor blades installed. AD 2003–08–
51 required reducing the retirement life
of each tail rotor blade (blade),
performing a one-time visual inspection
of each blade’s pitch horn (pitch horn)
for a crack or corrosion, and replacing
any cracked blade or any blade that has
exceeded its retirement life with an
SUMMARY:
E:\FR\FM\31OCR1.SGM
31OCR1
]]>Agencies
[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65178-65180]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25310]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0526; Directorate Identifier 2008-SW-14-AD;
Amendment 39-17633; AD 2013-22-01]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada (Bell)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Bell
Model 206L-4 and 407 helicopters. This AD requires replacing or
reworking certain aft bearing caps. This AD was
[[Page 65179]]
prompted by the manufacture of certain freewheel aft bearing caps
without a lubrication channel to allow oil flow into the aft bearing
support assembly. The actions of this AD are intended to prevent
failure of the freewheel unit and subsequent loss of control of the
helicopter.
DATES: This AD is effective December 5, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of December 5,
2013.
ADDRESSES: For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101,
telephone (817) 280-3391, fax (817) 280-6466. 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.
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: Eric Haight, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth,
Texas 76137, telephone (817) 222-5110, email: eric.haight@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 20, 2013, at 78 FR 37158, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to add an AD that would apply to Bell Model 206L-4 and 407
helicopters. The NPRM proposed to require, within 50 hours time-in-
service (TIS), removing and disassembling the freewheel assembly,
replacing the sprag, retainer, and the aft seal, and visually
inspecting the remaining freewheel part details for a missing channel.
Also, the NPRM proposed to require, if the channel is missing, before
further flight, replacing the cap assembly with an airworthy cap or
reworking and reidentifying the existing cap by using a vibrating
stylus to add the letter ``R'' to the serial number of the reworked
cap. The proposed actions were prompted by the manufacture of certain
freewheel aft bearing caps without a lubrication channel to allow oil
flow into the aft bearing support assembly. The proposed requirements
were intended to prevent failure of the freewheel unit and subsequent
loss of control of the helicopter.
The NPRM was prompted by AD No. CF-2004-17R1, dated February 11,
2005 (AD No. CF-2004-17R1), issued by TCAA, which is the aviation
authority for Canada. AD No. CF-2004-17R1 requires replacing or
reworking freewheel assemblies on the Bell Model 206L-4 and 407
helicopters. TCAA advises of a manufacturing oversight where a
lubrication channel was not machined into the aft bearing cap of some
freewheel units to allow oil flow into the aft bearing support
assembly. TCAA states that lack of lubrication may adversely affect the
durability and potentially the function of the freewheel unit.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 37158,
June 20, 2013).
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, TCAA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are issuing this AD because we evaluated all information
provided by TCAA 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 TCAA AD
This AD differs from the TCAA AD as follows:
We do not use a calendar time, which has already passed.
We require all affected helicopters to comply within 50
hours TIS; the TCAA AD has different compliance times as stipulated by
the calculated average engine start cycle count identified in the
applicable alert service bulletin (ASB), and a 300-hour TIS terminating
action for modifying all affected helicopters.
We do not require referencing compliance with the ASBs as
does the TCAA AD, and we do not require you to provide an affected cap
for rework to Bell Tennessee nor require the original cap to be
reworked by Bell Tennessee.
We do not require any action on ``spare'' parts not
installed on a helicopter but would require, before installing any
replacement bearing support assembly, ensuring that the rework has been
done.
Related Service Information
Bell has issued ASB No. 206L-04-129 for the Model 206L-4 and ASB
No. 407-04-66 for the Model 407, both Revision A, and both dated
December 1, 2004, which specify identifying the affected freewheel aft
bearing caps. The ASBs provide separate procedures, depending on
whether helicopters are ``not exclusively used for training'' or
``exclusively used for training,'' for replacing or reworking the
freewheel cap assembly and replacing the output shaft, part number (P/
N) 406-040-517-101, and sprag and retainer, P/N 406-040-580-103. TCCA
classified these ASBs as mandatory and issued AD No. CF-2004-17R to
ensure the continued airworthiness of these helicopters.
Costs of Compliance
We estimate there are 212 Model 206L-4 helicopters and 540 Model
407 helicopters of U.S. registry; however, we estimate that only 80
helicopters are affected by this AD. We estimate that operators may
incur the following costs in order to comply with this AD: It will take
about 16 work hours to replace the freewheel unit for all the affected
parts at an average labor rate of $85 per work hour. Required parts
will cost about $21,600 per helicopter. Based on these figures, we
estimate the total cost per helicopter will be $22,900, and the total
cost of the AD on U.S. operators will be $1,836,800.
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
[[Page 65180]]
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):
2013-22-01 Bell Helicopter Textron Canada: Amendment 39-17633;
Docket No. FAA-2013-0526; Directorate Identifier 2008-SW-14-AD.
(a) Applicability
This AD applies to Model 206L-4 and 407 helicopters, with a
freewheel aft bearing cap (cap), part number (P/N) 406-040-509-101,
with a serial number with a prefix of ``A-'' and Nos. 1833 through
1912, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as certain caps being
manufactured without a lubrication channel to allow oil flow into
the aft bearing support assembly, which could result in failure of
the freewheel unit and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 5, 2013.
(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
Within 50 hours time-in-service (TIS):
(1) Remove and disassemble each freewheel assembly.
(2) Replace the sprag and retainer (item 7), the output shaft
(item 10), and the aft seal (item 3), as depicted in Figure 2 of
Bell Alert Service Bulletin (ASB) No. 206L-04-129 for the Model
206L-4 and ASB No. 407-04-66 for the Model 407, both Revision A, and
both dated December 1, 2004.
(3) Visually inspect the remaining freewheel part details for a
missing channel.
(4) If the channel is missing, replace or rework the cap
assembly by following the instructions depicted in Figure 3 of ASB
206L-04-129 or ASB 407 04-66, as applicable for your model
helicopter. Using a vibrating stylus, mark the letter ``R'' at the
end of the serial number on the cap assembly.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Eric Haight, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group,
Fort Worth, Texas 76137, telephone (817) 222-5110, email:
eric.haight@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
The subject of this AD is addressed in Transport Canada Civil
Aviation (TCCA) AD No. CF-2004-17R1, dated February 11, 2005. You
may view the TCCA AD at https://www.regulations.gov in Docket No.
FAA-2013-0526.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor
Drive System.
(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 Alert Service Bulletin (ASB) No. 206L-04-129, Revision
A, dated December 1, 2004.
(ii) Bell ASB No. 407-04-66, Revision A, dated December 1, 2004.
(3) For Bell service information identified in this AD, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas
76101, telephone (817) 280-3391, fax (817) 280-6466.
(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 October 1, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-25310 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P
