Airworthiness Directives; Bell Helicopter Textron Canada Helicopters, 8358-8360 [2014-02954]
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Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
DEPARTMENT OF TRANSPORTATION
(o) Alternative Methods of Compliance
(AMOCs)
SUMMARY:
(1) The Manager, Fort Worth Airplane
Certification Office, 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (p) of this AD.
(2) 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.
(3) AMOCs approved for AD 2010–17–18
are approved as AMOCs for this AD.
(p) Related Information
tkelley on DSK3SPTVN1PROD with PROPOSALS
(1) For more information about this AD,
contact Andrew McAnaul, Aerospace
Engineer, ASW–150 (c/o MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308–3365; fax:
(210) 308–3370; email: andrew.mcanaul@
faa.gov.
(2) For service information identified in
this AD, contact Air Tractor, Inc., P.O. Box
485, Olney, Texas 76374; telephone: (940)
564–5616; fax: (940) 564–5612; email:
airmail@airtractor.com; Internet:
www.airtractor.com. You may review copies
of the referenced service information at the
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.
Issued in Kansas City, Missouri, on
February 5, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2014–03024 Filed 2–11–14; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
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Jkt 232001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0070; Directorate
Identifier 2011–SW–062–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Bell
Helicopter Textron Canada (BHTC)
Model 407 helicopters. This proposed
AD would require inspecting the aft
fuselage upper skin (upper skin) for a
crack and the upper left longeron
assembly (longeron assembly) for a
crack, corrosion, or defect. This AD
would require replacing or repairing a
part or section, depending on the
inspection’s outcome. This proposed
AD is prompted by reports of cracks in
the upper left-hand longeron. The
proposed actions are intended to
prevent failure of the longeron assembly
or the upper skin, which could lead to
a structural failure and loss of helicopter
control.
DATES: We must receive comments on
this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov 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 proposed AD, the
foreign authority’s AD, the economic
evaluation, any comments received, and
other information. The street address for
the Docket Operations Office (telephone
PO 00000
Frm 00032
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800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in
this proposed 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.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD No.
CF–2011–42, dated November 9, 2011,
to correct an unsafe condition for
certain BHTC Model 407 helicopters.
TCCA advises that longeron assemblies,
part numbers (P/Ns) 206–031–314–037,
206–031–314–177, and 206–031–314–
219B, installed on helicopters with
E:\FR\FM\12FEP1.SGM
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Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules
1,200 or more hours air time, are prone
to cracking. The TCCA AD requires,
based on hours air time since new,
visually inspecting the aft fuselage
upper skin for cracks and replacing the
skin if cracked. The TCCA AD also
requires visually inspecting the
longeron assembly for cracks and
general condition. If the longeron
assembly is serviceable, the TCCA AD
requires repeating the inspection of the
longeron assembly for cracks and
general condition at intervals based on
whether external strap doublers are
installed. If the longeron assembly is
cracked, the TCCA AD requires
repairing or replacing it, installing three
external strap doublers, and repeating
the inspection of the longeron assembly
if it was repaired. Installing a new
longeron assembly, P/N 206–031–314–
237B, and the three external strap
doublers constitutes terminating action
of the TCCA AD.
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, the TCCA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Related Service Information
BHTC has issued Alert Service
Bulletin 407–11–95, Revision C, dated
April 20, 2012 (ASB), to correct an
unsafe condition for Model 407
helicopters, serial numbers 53000
through 53900, 53911 through 54061,
and 54300, with a flight time of 1200 or
more hours, and with a longeron
assembly, P/N 206–031–314–037, 206–
031–314–177, or 206–031–314–219B.
The ASB states that BHTC received
reports of longeron assemblies cracking
in service. The ASB:
• Specifies a one-time inspection of
the aft fuselage top skin and repetitive
inspections of the upper left longeron
assembly;
• Provides a repair procedure for the
longeron assembly;
• Allows for the installation of
longeron assembly, P/N 206–031–314–
237B, and three external strap doublers
as terminating action for the repetitive
inspection requirements.
Proposed AD Requirements
We propose the following:
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Jkt 232001
Within 50 hours time-in-service (TIS),
or prior to reaching 1,250 hours TIS
since new, whichever occurs later,
visually inspect the upper skin for a
crack using a 10X or higher power
magnifying glass.
• If there is a crack in the upper skin,
before further flight, remove the skin
and inspect the longeron assembly,
paying attention to the upper flange, for
a crack, corrosion, or other damage
using a 10X or higher power magnifying
glass. If there are no cracks, corrosion,
or other damage in the longeron
assembly, before further flight, replace
the upper skin with an airworthy upper
skin. Repeat the inspection of the
longeron assembly at intervals not to
exceed 50 hours TIS. If there is a crack,
corrosion, or other damage in the
longeron assembly, before further flight:
Repair the longeron assembly or replace
it with an airworthy longeron assembly,
P/N 206–031–314–237B, and reinstall
the upper skin or replace it with an
airworthy upper skin. Install three
external strap doublers. Repeat the
inspection of the longeron assembly at
intervals not to exceed 50 hours TIS.
• If there is no crack in the upper
skin, within 10 hours TIS, visually
inspect the longeron assembly using a
10X or higher power magnifying glass
for a crack, corrosion, or other damage.
If there is a crack, corrosion, or other
damage in the longeron assembly, before
further flight: Repair the longeron
assembly or replace it with an airworthy
longeron assembly, P/N 206–031–314–
237B. Install three external strap
doublers. Repeat the inspection of the
upper skin and longeron assembly at
intervals not to exceed 50 hours TIS. If
there are no cracks, corrosion, or other
damage in the longeron assembly, repeat
the inspection of the upper skin and
longeron assembly at intervals not to
exceed 50 hours TIS.
• Replacing the longeron assembly
with longeron assembly, P/N 206–031–
314–237B, and installing three external
strap doublers constitutes terminating
action for this AD. If there is no crack
in the upper skin and no crack,
corrosion or other damage in the
longeron assembly, you may install
three external strap doublers, which
will extend the recurring 50 hours TIS
inspection interval to 150 hours TIS.
Costs of Compliance
We estimate that this proposed AD
would affect 584 helicopters of U.S.
Registry and that labor costs average $85
an hour. Based on these estimates, we
estimate the following costs:
A one-time visual inspection of the aft
fuselage upper skin would require 1
work-hour and no parts for a total cost
PO 00000
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Sfmt 4702
8359
of $85 per helicopter, $49,640 for the
U.S. fleet.
A visual inspection of the longeron
and replacing the aft fuselage upper skin
would require 3 work hours for a labor
cost of $255 per helicopter. Parts would
cost $723 for parts for total cost of $978
per helicopter.
Repairing the longeron if needed and
installing the doublers would require 16
work hours for a labor cost of $1,360.
Parts would cost $3,928 for a total cost
of $5,288 per helicopter.
Replacing the longeron with P/N 206–
031–314–237B combined with the
installation of the three external strap
doublers would require 24 work hours
for a labor cost of $2,040. Parts would
cost $13,560 for a total cost of $15,600
per helicopter.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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,
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Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Bell Helicopter Textron Canada: Docket No.
FAA–2014–0070; Directorate Identifier
2011–SW–062–AD.
(a) Applicability
This AD applies to Bell Helicopter Textron
Canada (BHTC) Model 407 helicopters, with
a serial number 53000 through 53900, 53911
through 54061, and 54300, with an upper left
longeron assembly (longeron assembly), part
number (P/N) 206–031–314–037, 206–031–
314–177, or 206–031–314–219B, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the aft fuselage upper skin or a
crack, corrosion, or defect in the longeron
assembly. This condition could cause
structural failure and consequently, loss of
helicopter control.
(c) Comments Due Date
We must receive comments by April 14,
2014.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(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), or
prior to reaching 1,250 hours TIS since new,
whichever occurs later, visually inspect the
helicopter’s aft fuselage upper skin (upper
skin) for a crack using a 10X or higher power
magnifying glass.
(1) If there is a crack in the upper skin,
before further flight, remove the skin and
inspect the longeron assembly, paying
attention to the upper flange, for a crack,
VerDate Mar<15>2010
16:19 Feb 11, 2014
Jkt 232001
corrosion, or other damage using a 10X or
higher power magnifying glass.
(i) If there are no cracks, corrosion, or other
damage in the longeron assembly, before
further flight, replace the upper skin with an
airworthy upper skin. Repeat the inspection
of the longeron assembly at intervals not to
exceed 50 hours TIS.
(ii) If there is a crack, corrosion, or other
damage in the longeron assembly, before
further flight:
(A) Repair the longeron assembly or
replace it with an airworthy longeron
assembly, part number (P/N) 206–031–314–
237B, and reinstall the upper skin or replace
it with an airworthy upper skin.
(B) Install three external strap doublers in
accordance with Part III, paragraphs 5
through10 of Bell Alert Service Bulletin 407–
11–95, Revision C, dated April 20, 2012
(ASB).
(C) Repeat the inspection of the longeron
assembly at intervals not to exceed 50 hours
TIS.
(2) If there is no crack in the upper skin,
within 10 hours TIS, visually inspect the
longeron assembly using a 10X or higher
power magnifying glass for a crack,
corrosion, or other damage.
(i) If there is a crack, corrosion, or other
damage in the longeron assembly, before
further flight:
(A) Repair the longeron assembly or
replace it with an airworthy longeron
assembly, P/N 206–031–314–237B.
(B) Install three external strap doublers in
accordance with Part III, paragraphs 5
through 10 of the ASB.
(C) Repeat the inspection of the upper skin
and longeron assembly at intervals not to
exceed 50 hours TIS.
(ii) If there are no cracks, corrosion, or
other damage in the longeron assembly,
repeat the inspection of the upper skin and
longeron assembly at intervals not to exceed
50 hours TIS.
(3) Replacing the longeron assembly with
longeron assembly, P/N 206–031–314–237B,
and installing three external strap doublers
constitutes terminating action for this AD.
(4) If there is no crack in the upper skin
and there is no crack, corrosion, or other
damage in the longeron assembly, you may
install three external strap doublers in
accordance with Part III, paragraphs 5
through 10 of the ASB. This option extends
the recurring 50 hours TIS inspection
interval to 150 hours TIS.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; 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
PO 00000
Frm 00034
Fmt 4702
Sfmt 4702
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–2011–42, dated November 9, 2011.
You may view the TCCA AD in the AD
docket on the Internet at
https://www.regulations.gov.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 5313, Fuselage Main, Longeron/
Stringer.
Issued in Fort Worth, Texas, on January 31,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–02954 Filed 2–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2013–0806; Airspace
Docket No. 13–ASO–21]
Proposed Amendment of Class D and
Class E Airspace, and Proposed
Establishment of Class E Airspace; TriCities, TN
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Class D and Class E Airspace,
and establish Class E airspace at TriCities Regional Airport, Tri-Cities, TN.
Airspace reconfiguration would
alleviate traffic issues in the
surrounding area for Johnson City
Airport and Edwards Heliport so flights
could navigate in and out of their
respective airports in Visual Flight
Rules conditions under 700 feet. This
would enhance the safety and airspace
management of Instrument Flight Rules
(IFR) operations in the area.
DATES: Comments must be received on
or before March 31, 2014.
ADDRESSES: Send comments on this rule
to: U.S. Department of Transportation,
Docket Operations, West Building
Ground Floor, Room W12–140, 1200
New Jersey SE., Washington, DC 20590–
0001; Telephone: 1–800–647–5527; Fax:
202–493–2251. You must identify the
Docket Number FAA–2013–0806;
Airspace Docket No. 13–ASO–21, at the
beginning of your comments. You may
also submit and review received
SUMMARY:
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]]>Agencies
[Federal Register Volume 79, Number 29 (Wednesday, February 12, 2014)]
[Proposed Rules]
[Pages 8358-8360]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02954]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0070; Directorate Identifier 2011-SW-062-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This
proposed AD would require inspecting the aft fuselage upper skin (upper
skin) for a crack and the upper left longeron assembly (longeron
assembly) for a crack, corrosion, or defect. This AD would require
replacing or repairing a part or section, depending on the inspection's
outcome. This proposed AD is prompted by reports of cracks in the upper
left-hand longeron. The proposed actions are intended to prevent
failure of the longeron assembly or the upper skin, which could lead to
a structural failure and loss of helicopter control.
DATES: We must receive comments on this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov 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 proposed AD, the foreign
authority's AD, the economic evaluation, any comments received, and
other information. The street address for the Docket Operations Office
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed 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.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD No. CF-2011-42, dated
November 9, 2011, to correct an unsafe condition for certain BHTC Model
407 helicopters. TCCA advises that longeron assemblies, part numbers
(P/Ns) 206-031-314-037, 206-031-314-177, and 206-031-314-219B,
installed on helicopters with
[[Page 8359]]
1,200 or more hours air time, are prone to cracking. The TCCA AD
requires, based on hours air time since new, visually inspecting the
aft fuselage upper skin for cracks and replacing the skin if cracked.
The TCCA AD also requires visually inspecting the longeron assembly for
cracks and general condition. If the longeron assembly is serviceable,
the TCCA AD requires repeating the inspection of the longeron assembly
for cracks and general condition at intervals based on whether external
strap doublers are installed. If the longeron assembly is cracked, the
TCCA AD requires repairing or replacing it, installing three external
strap doublers, and repeating the inspection of the longeron assembly
if it was repaired. Installing a new longeron assembly, P/N 206-031-
314-237B, and the three external strap doublers constitutes terminating
action of the TCCA AD.
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, the TCCA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other products of the same type design.
Related Service Information
BHTC has issued Alert Service Bulletin 407-11-95, Revision C, dated
April 20, 2012 (ASB), to correct an unsafe condition for Model 407
helicopters, serial numbers 53000 through 53900, 53911 through 54061,
and 54300, with a flight time of 1200 or more hours, and with a
longeron assembly, P/N 206-031-314-037, 206-031-314-177, or 206-031-
314-219B. The ASB states that BHTC received reports of longeron
assemblies cracking in service. The ASB:
Specifies a one-time inspection of the aft fuselage top
skin and repetitive inspections of the upper left longeron assembly;
Provides a repair procedure for the longeron assembly;
Allows for the installation of longeron assembly, P/N 206-
031-314-237B, and three external strap doublers as terminating action
for the repetitive inspection requirements.
Proposed AD Requirements
We propose the following:
Within 50 hours time-in-service (TIS), or prior to reaching 1,250
hours TIS since new, whichever occurs later, visually inspect the upper
skin for a crack using a 10X or higher power magnifying glass.
If there is a crack in the upper skin, before further
flight, remove the skin and inspect the longeron assembly, paying
attention to the upper flange, for a crack, corrosion, or other damage
using a 10X or higher power magnifying glass. If there are no cracks,
corrosion, or other damage in the longeron assembly, before further
flight, replace the upper skin with an airworthy upper skin. Repeat the
inspection of the longeron assembly at intervals not to exceed 50 hours
TIS. If there is a crack, corrosion, or other damage in the longeron
assembly, before further flight: Repair the longeron assembly or
replace it with an airworthy longeron assembly, P/N 206-031-314-237B,
and reinstall the upper skin or replace it with an airworthy upper
skin. Install three external strap doublers. Repeat the inspection of
the longeron assembly at intervals not to exceed 50 hours TIS.
If there is no crack in the upper skin, within 10 hours
TIS, visually inspect the longeron assembly using a 10X or higher power
magnifying glass for a crack, corrosion, or other damage. If there is a
crack, corrosion, or other damage in the longeron assembly, before
further flight: Repair the longeron assembly or replace it with an
airworthy longeron assembly, P/N 206-031-314-237B. Install three
external strap doublers. Repeat the inspection of the upper skin and
longeron assembly at intervals not to exceed 50 hours TIS. If there are
no cracks, corrosion, or other damage in the longeron assembly, repeat
the inspection of the upper skin and longeron assembly at intervals not
to exceed 50 hours TIS.
Replacing the longeron assembly with longeron assembly, P/
N 206-031-314-237B, and installing three external strap doublers
constitutes terminating action for this AD. If there is no crack in the
upper skin and no crack, corrosion or other damage in the longeron
assembly, you may install three external strap doublers, which will
extend the recurring 50 hours TIS inspection interval to 150 hours TIS.
Costs of Compliance
We estimate that this proposed AD would affect 584 helicopters of
U.S. Registry and that labor costs average $85 an hour. Based on these
estimates, we estimate the following costs:
A one-time visual inspection of the aft fuselage upper skin would
require 1 work-hour and no parts for a total cost of $85 per
helicopter, $49,640 for the U.S. fleet.
A visual inspection of the longeron and replacing the aft fuselage
upper skin would require 3 work hours for a labor cost of $255 per
helicopter. Parts would cost $723 for parts for total cost of $978 per
helicopter.
Repairing the longeron if needed and installing the doublers would
require 16 work hours for a labor cost of $1,360. Parts would cost
$3,928 for a total cost of $5,288 per helicopter.
Replacing the longeron with P/N 206-031-314-237B combined with the
installation of the three external strap doublers would require 24 work
hours for a labor cost of $2,040. Parts would cost $13,560 for a total
cost of $15,600 per helicopter.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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,
[[Page 8360]]
on a substantial number of small entities under the criteria of the
Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Bell Helicopter Textron Canada: Docket No. FAA-2014-0070;
Directorate Identifier 2011-SW-062-AD.
(a) Applicability
This AD applies to Bell Helicopter Textron Canada (BHTC) Model
407 helicopters, with a serial number 53000 through 53900, 53911
through 54061, and 54300, with an upper left longeron assembly
(longeron assembly), part number (P/N) 206-031-314-037, 206-031-314-
177, or 206-031-314-219B, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the aft
fuselage upper skin or a crack, corrosion, or defect in the longeron
assembly. This condition could cause structural failure and
consequently, loss of helicopter control.
(c) Comments Due Date
We must receive comments by April 14, 2014.
(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), or prior to reaching
1,250 hours TIS since new, whichever occurs later, visually inspect
the helicopter's aft fuselage upper skin (upper skin) for a crack
using a 10X or higher power magnifying glass.
(1) If there is a crack in the upper skin, before further
flight, remove the skin and inspect the longeron assembly, paying
attention to the upper flange, for a crack, corrosion, or other
damage using a 10X or higher power magnifying glass.
(i) If there are no cracks, corrosion, or other damage in the
longeron assembly, before further flight, replace the upper skin
with an airworthy upper skin. Repeat the inspection of the longeron
assembly at intervals not to exceed 50 hours TIS.
(ii) If there is a crack, corrosion, or other damage in the
longeron assembly, before further flight:
(A) Repair the longeron assembly or replace it with an airworthy
longeron assembly, part number (P/N) 206-031-314-237B, and reinstall
the upper skin or replace it with an airworthy upper skin.
(B) Install three external strap doublers in accordance with
Part III, paragraphs 5 through10 of Bell Alert Service Bulletin 407-
11-95, Revision C, dated April 20, 2012 (ASB).
(C) Repeat the inspection of the longeron assembly at intervals
not to exceed 50 hours TIS.
(2) If there is no crack in the upper skin, within 10 hours TIS,
visually inspect the longeron assembly using a 10X or higher power
magnifying glass for a crack, corrosion, or other damage.
(i) If there is a crack, corrosion, or other damage in the
longeron assembly, before further flight:
(A) Repair the longeron assembly or replace it with an airworthy
longeron assembly, P/N 206-031-314-237B.
(B) Install three external strap doublers in accordance with
Part III, paragraphs 5 through 10 of the ASB.
(C) Repeat the inspection of the upper skin and longeron
assembly at intervals not to exceed 50 hours TIS.
(ii) If there are no cracks, corrosion, or other damage in the
longeron assembly, repeat the inspection of the upper skin and
longeron assembly at intervals not to exceed 50 hours TIS.
(3) Replacing the longeron assembly with longeron assembly, P/N
206-031-314-237B, and installing three external strap doublers
constitutes terminating action for this AD.
(4) If there is no crack in the upper skin and there is no
crack, corrosion, or other damage in the longeron assembly, you may
install three external strap doublers in accordance with Part III,
paragraphs 5 through 10 of the ASB. This option extends the
recurring 50 hours TIS inspection interval to 150 hours TIS.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; 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.
(g) Additional Information
The subject of this AD is addressed in Transport Canada Civil
Aviation (TCCA) AD No. CF-2011-42, dated November 9, 2011. You may
view the TCCA AD in the AD docket on the Internet at https://www.regulations.gov.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 5313, Fuselage
Main, Longeron/Stringer.
Issued in Fort Worth, Texas, on January 31, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-02954 Filed 2-11-14; 8:45 am]
BILLING CODE 4910-13-P
