Airworthiness Directives; Bell Helicopter Textron Canada Helicopters, 38546-38550 [2013-14857]
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Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2012–0270, dated
December 20, 2012, for related information,
which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(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) Britten-Norman Service Bulletin
Number SB 332, Issue 1, dated December 6,
2012.
(ii) Reserved.
(3) For B–N Group Ltd. service information
identified in this AD, contact Britten-Norman
Aircraft Ltd, Commodore House,
Mountbatten Business Centre, Millbrook
Road East, Southampton SO15 1HY, United
Kingdom; telephone: +44 01983 872511; fax:
+44 01983 873246; email:
info@bnaircraft.com; Internet: www.brittennorman.com.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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 Kansas City, Missouri, on June
18, 2013.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–14979 Filed 6–26–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0019; Directorate
Identifier 2010–SW–051–AD; Amendment
39–17485; AD 2013–12–07]
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RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
SUMMARY:
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Helicopter Textron Canada (BHTC)
Model 407 helicopters with certain
tailboom assemblies installed. This AD
requires, at specified intervals,
inspecting the tailboom assembly for a
crack, loose rivet, or other damage. This
AD was prompted by a stress analysis of
the tailboom skin that revealed that
high-stress-concentration areas are
susceptible to skin cracking. This
condition, if not detected, could result
in a crack in the tailboom assembly,
failure of the tailboom, and subsequent
loss of control of the helicopter.
DATES: This AD is effective August 1,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of August 1, 2013.
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.
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, 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:
Sharon Miles, Aerospace Engineer,
FAA, Regulations and Policy Group,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; fax
(817) 222–5110; email
sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada, which is the
aviation authority for Canada, has
issued AD CF–2009–07, dated March 6,
2009 (AD CF–2009–07), to correct an
unsafe condition for the BHTC Model
407 helicopters with a tailboom
assembly, part number (P/N) 407–030–
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Fmt 4700
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801–201, –203, or –205. Transport
Canada states that a stress analysis of
the chemically milled tailboom skin
‘‘revealed a possibility of skin cracking
due to high stress concentration areas.’’
Transport Canada advises that this
condition, if not detected, could result
in ‘‘serious damage to the tailboom.’’
On February 1, 2013, at 78 FR 7308,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 to include an AD that would apply
to BHTC Model 407 helicopters, with
tailboom assembly part number (P/N)
407–030–801–201, 407–030–801–203,
or 407–030–801–205. The NPRM
proposed to require, at specified
intervals, inspecting the tailboom
assembly for a crack, loose rivet, or
other damage. The proposed
requirements were intended to prevent
a crack in the tailboom assembly, failure
of the tailboom, and subsequent loss of
control of the helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(78 FR 7308, February 1, 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, Transport
Canada, 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 Canada and
determined that an 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
Transport Canada AD
The Transport Canada AD states to
perform the inspections of the tailboom
‘‘in accordance with inspection
procedures as per applicable part’’ of
the ASB. This proposed AD references
only specific sections of the ASB for
accomplishing the requirements.
Related Service Information
BHTC has issued Alert Service
Bulletin No. 407–08–84, dated August
18, 2008 (ASB), which specifies a new
inspection schedule for the tailboom
assemblies. BHTC states it has not
received any field reports indicating
cracked skin in service on the tailboom
assemblies. However, in the interest of
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safety, BHTC states it has elected to
introduce a new inspection schedule for
the tailboom assemblies. The ASB
specifies the new inspection schedule.
Transport Canada classified this ASB as
mandatory and issued AD CF–2009–07
to ensure the continued airworthiness of
these helicopters.
Costs of Compliance
We estimate that this AD will affect
551 helicopters of U.S. registry, and
estimate the cost of compliance for the
first year as follows:
• We assume 1 initial 100-hour TIS
inspection and 2 recurring inspections,
which will each take about 2.5 hours. At
an average labor rate of $85 per hour,
this will result in a cost of about $213
per inspection per helicopter or a total
annual inspection cost for 3 recurring
inspections of about $639 per
helicopter.
• We assume 1 initial inspection and
thereafter 4 recurring inspections per
year for helicopters with a tailboom
assembly that has 6,900 or more hours
TIS, which will each take 3 hours at the
average labor rate of $85 per hour or
$255 per helicopter. Multiplying this
$255 times the 5 recurring inspections,
the total annual cost will be $1,275 per
helicopter.
• We assume 1 initial inspection and
12 recurring inspections per year for
helicopters with a tailboom assembly
that has 8,600 or more hours TIS. If each
inspection takes 3.25 hours, at the
average labor rate of $85 per hour, each
inspection will cost about $276.
Multiply $276 times the 13 recurring
inspections will result in a total annual
inspection cost of $3,588 per helicopter.
We expect the cost of pilot checks to be
minimal.
• Replacing the tailboom will take 10
work hours at an average labor rate of
$85 per hour for a total labor cost of
$850 per helicopter. Parts will cost
$82,850 for a total cost per helicopter of
$83,700. Assuming that 5 helicopters
per year will need a replacement
tailboom, the fleet replacement cost will
total $418,500.
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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,
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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,
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38547
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):
■
2013–12–07 Bell Helicopter Textron
Canada (BHTC): Amendment 39–17485;
Docket No. FAA–2013–0019; Directorate
Identifier 2010–SW–051–AD.
(a) Applicability
This AD applies to BHTC Model 407
helicopters, with tailboom assembly part
number (P/N) 407–030–801–201, 407–030–
801–203, or 407–030–801–205, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
high-stress-concentration areas in the
tailboom skin that are at risk of cracking.
This condition could result in a crack in the
tailboom assembly, failure of the tailboom,
and subsequent loss of helicopter control.
(c) Effective Date
This AD becomes effective August 1, 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
(1) For helicopters with a tailboom
assembly that has 8,600 or more hours timein-service (TIS):
(i) Comply with either paragraph
(e)(1)(i)(A) or (e)(1)(i)(B):
(A) Before the first flight of each day,
visually check for a crack in the ‘‘C’’ and ‘‘D’’
areas depicted in Figures 1and 2 to Paragraph
(e) of this AD. The actions required by this
paragraph may be performed by the owner/
operator (pilot) holding at least a private pilot
certificate, and must be entered into the
aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9
(a)(1)–(4) and 14 CFR § 91.417(a)(2)(v). The
record must be maintained as required by 14
CFR 91.417, 121.380, or 135.439; or
BILLING CODE 4910–13–P
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Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations
TAILBOOM IDENTIFICATION PLATE R
AREAB
39.00
ftEf
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Figure 1 to Paragraph (e)
Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations
(B) Within 25 hours TIS, or 30 days,
whichever comes first, and thereafter at
intervals not to exceed 50 hours TIS, clean
and inspect for a crack around each fastener
and just above the edge of the upper
stabilizer support in the ‘‘C’’ and ‘‘D’’ areas
on the left side of the tailboom assembly, as
depicted in Figure 2 to Paragraph (e) of this
AD, using a 10X or higher power magnifying
glass.
(ii) Comply with the requirements of
paragraph (e)(2)(i)(A) or (e)(2)(i)(B), and
paragraph (e)(3) of this AD.
(2) For helicopters with a tailboom
assembly that has 6,900 or more hours TIS:
(i) Within 25 hours TIS or 30 days,
whichever occurs first, clean and inspect the
tailboom assembly for a crack in the ‘‘H’’ and
‘‘I’’ areas depicted in Figure 2, Sheet 5, of the
BHTC Alert Service Bulletin No. 407–08–84,
dated August 18, 2008, (ASB), by using one
of the two following methods.
(A) Use a 10X or higher power magnifying
glass; thereafter, repeat the 10X or higher
power magnifying glass inspection at
intervals not to exceed 150 hours TIS; or
(B) Eddy current inspect for a crack in
accordance with Appendix A and Table 1,
and by referencing Figures 3 through 7 of the
ASB; thereafter, repeat the eddy current
inspection at intervals not to exceed 500
hours TIS. Use a person qualified to Level II
or Level III per the National Aerospace
Standard (NAS) 410 or equivalent
requirements to perform the eddy current
inspection.
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(ii) Comply with the requirements of
paragraph (e)(3) of this AD.
(3) Within 100 hours TIS or at the next
tailboom inspection, whichever comes first,
and thereafter at intervals not to exceed 300
hours TIS:
(i) Clean and inspect the tailboom
assembly for a loose rivet, a crack, or other
damage in accordance with Part II,
paragraphs 2 and 3, of the ASB; and
(ii) Using a 10X or higher power
magnifying glass, inspect the tailboom
assembly for a loose rivet or a crack in
accordance with Part II, paragraphs 4 through
6, of the ASB.
(4) If the total accumulated hours TIS on
the tailboom assembly is unknown, assume
the tailboom assembly has 8,600 or more
hours TIS and clean and inspect in
accordance with paragraph (e)(1) of this AD.
(5) If there is a crack in the tailboom
assembly, before further flight, replace it with
an airworthy tailboom assembly.
(f) Special Flight Permits
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the requirements of this AD can be
accomplished, provided no passenger is on
board and any crack or damage is temporarily
repaired using FAA-approved procedures.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
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Aerospace Engineer, FAA, Regulations and
Policy Group, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5110; fax (817) 222–5961; email
sharon.y.miles@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.
(h) Additional Information
The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
No. CF–2009–07, dated March 6, 2009. You
may view the TCCA AD at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–0019.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5302, rotorcraft tailboom.
(j) 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 Textron Canada Alert
Service Bulletin No. 407–08–84, dated
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Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations
August 18, 2008, excluding Figure 2 sheets
1 and 4.
(ii) Reserved.
(3) For BHTC 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 3,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–14857 Filed 6–26–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0205; Directorate
Identifier 2012–NM–226–AD; Amendment
39–17493; AD 2013–13–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 747SP series
airplanes, and certain The Boeing
SUMMARY:
Company Model 747–100B SUD and
747–300 series airplanes. This AD was
prompted by an evaluation by the
design approval holder indicating that
the fuselage skin just above certain lap
splice locations is subject to widespread
fatigue damage. This AD requires
repetitive inspections for cracking of the
fuselage skin above certain lap splice
locations, and repair if necessary. We
are issuing this AD to detect and correct
fatigue cracking of the fuselage skin,
which could result in reduced structural
integrity of the airplane and sudden loss
of cabin pressure.
DATES: This AD is effective August 1,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 1, 2013.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6428;
fax: 425–917–6590; email:
Nathan.P.Weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM published in the Federal
Register on March 7, 2013 (78 FR
14719). That NPRM proposed to require
repetitive inspections for cracking of the
fuselage skin above certain lap splice
locations, and repair if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Boeing supported the NPRM (78 FR
14719, March 7, 2013).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
as proposed–except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
14719, March 7, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 14719,
March 7, 2013).
Costs of Compliance
We estimate that this AD affects 4
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Parts
cost
Labor cost
Inspection ............................................
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Action
Up to 57 work-hours × $85 per hour
= $4,845, per inspection cycle.
We have received no definitive data
that would enable us to provide
coststimates for the on-condition actions
specified in this AD.
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Jkt 229001
$0
Cost per product
Cost on U.S. operators
Up to $4,845, per inspection cycle.
Up to $19,380, per inspection cycle.
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
PO 00000
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Sfmt 4700
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,
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]]>Agencies
[Federal Register Volume 78, Number 124 (Thursday, June 27, 2013)]
[Rules and Regulations]
[Pages 38546-38550]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-14857]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0019; Directorate Identifier 2010-SW-051-AD;
Amendment 39-17485; AD 2013-12-07]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada
Helicopters
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 407 helicopters with certain
tailboom assemblies installed. This AD requires, at specified
intervals, inspecting the tailboom assembly for a crack, loose rivet,
or other damage. This AD was prompted by a stress analysis of the
tailboom skin that revealed that high-stress-concentration areas are
susceptible to skin cracking. This condition, if not detected, could
result in a crack in the tailboom assembly, failure of the tailboom,
and subsequent loss of control of the helicopter.
DATES: This AD is effective August 1, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of August 1, 2013.
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.
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, 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: Sharon Miles, Aerospace Engineer, FAA,
Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222-5110; fax (817) 222-5110; email
sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada, which is the aviation authority for Canada, has
issued AD CF-2009-07, dated March 6, 2009 (AD CF-2009-07), to correct
an unsafe condition for the BHTC Model 407 helicopters with a tailboom
assembly, part number (P/N) 407-030-801-201, -203, or -205. Transport
Canada states that a stress analysis of the chemically milled tailboom
skin ``revealed a possibility of skin cracking due to high stress
concentration areas.'' Transport Canada advises that this condition, if
not detected, could result in ``serious damage to the tailboom.''
On February 1, 2013, at 78 FR 7308, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to BHTC Model 407
helicopters, with tailboom assembly part number (P/N) 407-030-801-201,
407-030-801-203, or 407-030-801-205. The NPRM proposed to require, at
specified intervals, inspecting the tailboom assembly for a crack,
loose rivet, or other damage. The proposed requirements were intended
to prevent a crack in the tailboom assembly, failure of the tailboom,
and subsequent loss of control of the helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (78 FR 7308, February
1, 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, Transport Canada, 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 Canada and determined that an 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 Transport Canada AD
The Transport Canada AD states to perform the inspections of the
tailboom ``in accordance with inspection procedures as per applicable
part'' of the ASB. This proposed AD references only specific sections
of the ASB for accomplishing the requirements.
Related Service Information
BHTC has issued Alert Service Bulletin No. 407-08-84, dated August
18, 2008 (ASB), which specifies a new inspection schedule for the
tailboom assemblies. BHTC states it has not received any field reports
indicating cracked skin in service on the tailboom assemblies. However,
in the interest of
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safety, BHTC states it has elected to introduce a new inspection
schedule for the tailboom assemblies. The ASB specifies the new
inspection schedule. Transport Canada classified this ASB as mandatory
and issued AD CF-2009-07 to ensure the continued airworthiness of these
helicopters.
Costs of Compliance
We estimate that this AD will affect 551 helicopters of U.S.
registry, and estimate the cost of compliance for the first year as
follows:
We assume 1 initial 100-hour TIS inspection and 2
recurring inspections, which will each take about 2.5 hours. At an
average labor rate of $85 per hour, this will result in a cost of about
$213 per inspection per helicopter or a total annual inspection cost
for 3 recurring inspections of about $639 per helicopter.
We assume 1 initial inspection and thereafter 4 recurring
inspections per year for helicopters with a tailboom assembly that has
6,900 or more hours TIS, which will each take 3 hours at the average
labor rate of $85 per hour or $255 per helicopter. Multiplying this
$255 times the 5 recurring inspections, the total annual cost will be
$1,275 per helicopter.
We assume 1 initial inspection and 12 recurring
inspections per year for helicopters with a tailboom assembly that has
8,600 or more hours TIS. If each inspection takes 3.25 hours, at the
average labor rate of $85 per hour, each inspection will cost about
$276. Multiply $276 times the 13 recurring inspections will result in a
total annual inspection cost of $3,588 per helicopter. We expect the
cost of pilot checks to be minimal.
Replacing the tailboom will take 10 work hours at an
average labor rate of $85 per hour for a total labor cost of $850 per
helicopter. Parts will cost $82,850 for a total cost per helicopter of
$83,700. Assuming that 5 helicopters per year will need a replacement
tailboom, the fleet replacement cost will total $418,500.
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):
2013-12-07 Bell Helicopter Textron Canada (BHTC): Amendment 39-
17485; Docket No. FAA-2013-0019; Directorate Identifier 2010-SW-051-
AD.
(a) Applicability
This AD applies to BHTC Model 407 helicopters, with tailboom
assembly part number (P/N) 407-030-801-201, 407-030-801-203, or 407-
030-801-205, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as high-stress-
concentration areas in the tailboom skin that are at risk of
cracking. This condition could result in a crack in the tailboom
assembly, failure of the tailboom, and subsequent loss of helicopter
control.
(c) Effective Date
This AD becomes effective August 1, 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
(1) For helicopters with a tailboom assembly that has 8,600 or
more hours time-in-service (TIS):
(i) Comply with either paragraph (e)(1)(i)(A) or (e)(1)(i)(B):
(A) Before the first flight of each day, visually check for a
crack in the ``C'' and ``D'' areas depicted in Figures 1and 2 to
Paragraph (e) of this AD. The actions required by this paragraph may
be performed by the owner/operator (pilot) holding at least a
private pilot certificate, and must be entered into the aircraft
records showing compliance with this AD in accordance with 14 CFR
43.9 (a)(1)-(4) and 14 CFR Sec. 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417, 121.380, or 135.439; or
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(B) Within 25 hours TIS, or 30 days, whichever comes first, and
thereafter at intervals not to exceed 50 hours TIS, clean and
inspect for a crack around each fastener and just above the edge of
the upper stabilizer support in the ``C'' and ``D'' areas on the
left side of the tailboom assembly, as depicted in Figure 2 to
Paragraph (e) of this AD, using a 10X or higher power magnifying
glass.
(ii) Comply with the requirements of paragraph (e)(2)(i)(A) or
(e)(2)(i)(B), and paragraph (e)(3) of this AD.
(2) For helicopters with a tailboom assembly that has 6,900 or
more hours TIS:
(i) Within 25 hours TIS or 30 days, whichever occurs first,
clean and inspect the tailboom assembly for a crack in the ``H'' and
``I'' areas depicted in Figure 2, Sheet 5, of the BHTC Alert Service
Bulletin No. 407-08-84, dated August 18, 2008, (ASB), by using one
of the two following methods.
(A) Use a 10X or higher power magnifying glass; thereafter,
repeat the 10X or higher power magnifying glass inspection at
intervals not to exceed 150 hours TIS; or
(B) Eddy current inspect for a crack in accordance with Appendix
A and Table 1, and by referencing Figures 3 through 7 of the ASB;
thereafter, repeat the eddy current inspection at intervals not to
exceed 500 hours TIS. Use a person qualified to Level II or Level
III per the National Aerospace Standard (NAS) 410 or equivalent
requirements to perform the eddy current inspection.
(ii) Comply with the requirements of paragraph (e)(3) of this
AD.
(3) Within 100 hours TIS or at the next tailboom inspection,
whichever comes first, and thereafter at intervals not to exceed 300
hours TIS:
(i) Clean and inspect the tailboom assembly for a loose rivet, a
crack, or other damage in accordance with Part II, paragraphs 2 and
3, of the ASB; and
(ii) Using a 10X or higher power magnifying glass, inspect the
tailboom assembly for a loose rivet or a crack in accordance with
Part II, paragraphs 4 through 6, of the ASB.
(4) If the total accumulated hours TIS on the tailboom assembly
is unknown, assume the tailboom assembly has 8,600 or more hours TIS
and clean and inspect in accordance with paragraph (e)(1) of this
AD.
(5) If there is a crack in the tailboom assembly, before further
flight, replace it with an airworthy tailboom assembly.
(f) Special Flight Permits
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished, provided no passenger
is on board and any crack or damage is temporarily repaired using
FAA-approved procedures.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Sharon Miles, Aerospace
Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd.,
Fort Worth, Texas 76137; telephone (817) 222-5110; fax (817) 222-
5961; email sharon.y.miles@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.
(h) Additional Information
The subject of this AD is addressed in Transport Canada Civil
Aviation (TCCA) AD No. CF-2009-07, dated March 6, 2009. You may view
the TCCA AD at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2013-0019.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5302, rotorcraft
tailboom.
(j) 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 Textron Canada Alert Service Bulletin No.
407-08-84, dated
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August 18, 2008, excluding Figure 2 sheets 1 and 4.
(ii) Reserved.
(3) For BHTC 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 3, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-14857 Filed 6-26-13; 8:45 am]
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