Airworthiness Directives; Bell Helicopter Textron Canada Models 206L, L-1, L-3, L-4, and 407 Helicopters, 12303-12305 [E8-4495]
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Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
information for accomplishing the
modification in paragraph (g) of this AD.
1. The authority citation for part 39
continues to read as follows:
Modification
(g) At the applicable compliance time
specified in paragraph (g)(1) or (g)(2) of this
AD, modify the fuel boost pumps having part
numbers 60–847–1A, –2, and –3, in
accordance with the Accomplishment
Instructions of the applicable service
bulletin.
(1) For fuel boost pumps identified as
Configuration 1 or 2 in Table 1 of paragraph
1.E. of the applicable service bulletin, do the
modification within 120 months after the
effective date of this AD.
(2) For fuel boost pumps identified as
Configuration 3 in Table 1 of paragraph 1.E.
of the applicable service bulletin, do the
modification within 72 months after the
effective date of this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
McDonnell Douglas: Docket No. FAA–2007–
27339; Directorate Identifier 2006–NM–
280–AD.
Comments Due Date
(a) We must receive comments by April 1,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) McDonnell Douglas Model DC–10–10
and DC–10–10F airplanes, Model DC–10–15
airplanes, Model DC–10–30 and DC–10–30F
(KC–10A and KDC–10) airplanes, Model DC–
10–40 and DC–10–40F airplanes, and Model
MD–10–10F and MD–10–30F airplanes; as
identified in Boeing Alert Service Bulletin
DC10–28A254, Revision 1, dated September
12, 2007.
(2) McDonnell Douglas Model MD–11 and
MD–11F airplanes, as identified in Boeing
Alert Service Bulletin MD11–28A134,
Revision 1, dated September 6, 2007.
Unsafe Condition
(d) This AD results from a fuel boost pump
found with blown thermal fuses and a
fractured thrust washer. We are issuing this
AD to prevent failure of the fuel boost
pumps, which could lead to the potential of
ignition sources inside fuel tanks. This
condition, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
rwilkins on PROD1PC63 with PROPOSALS
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the following service
bulletins, as applicable:
(1) For the airplanes identified in
paragraph (c)(1) of this AD, Boeing Alert
Service Bulletin DC10–28A254, Revision 1,
dated September 12, 2007.
(2) For the airplanes identified in
paragraph (c)(2) of this AD, Boeing Alert
Service Bulletin MD11–28A134, Revision 1,
dated September 6, 2007.
Note 1: Boeing Alert Service Bulletin
DC10–28A254, Revision 1, dated September
12, 2007; and Boeing Alert Service Bulletin
MD11–28A134, Revision 1, dated September
6, 2007; refer to Crane Hydro-Aire Service
Bulletin 60–847–28–3, Revision 1, dated July
2, 2007, as an additional source of service
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17:21 Mar 06, 2008
Jkt 214001
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, ATTN: Samuel
Lee, Aerospace Engineer, Propulsion Branch,
ANM–140L, 3960 Paramount Boulevard,
Lakewood, California 90712–4137; telephone
(562) 627–5262; fax (562) 627–5210; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on March 3,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4475 Filed 3–6–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0258; Directorate
Identifier 2007–SW–22–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Models
206L, L–1, L–3, L–4, and 407
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
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12303
specified Bell Helicopter Textron
Canada (BHTC) helicopters. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The Aviation
Authority of Canada with whom we
have a bilateral agreement states in the
MCAI:
Horizontal stabilizers part numbers 206–
023–119–167 and 407–023–801–109 may
have manufacturing flaws on the inside
surface of the upper and/or lower skin at the
tailboom attachment inserts. These flaws may
result in cracking of the skin and failure of
the horizontal stabilizer.
The manufacturer’s service
information states that in addition to
cracks, the horizontal stabilizer may
have deformation or debonding around
and between the inserts. The proposed
AD would require actions that are
intended to address all these unsafe
conditions.
DATES: We must receive comments on
this proposed AD by April 7, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, 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
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 FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
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Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0258; Directorate Identifier
2007–SW–22–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
rwilkins on PROD1PC63 with PROPOSALS
Discussion
Transport Canada, which is the
aviation authority for Canada, has
issued an MCAI in the form of Canadian
Airworthiness Directive No. CF–2007–
03, dated March 27, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for these Canadiancertificated products. The MCAI states:
Horizontal stabilizers part numbers 206–
023–119–167 and 407–023–801–109 may
have manufacturing flaws on the inside
surface of the upper and/or lower skin at the
tailboom attachment inserts. These flaws may
result in cracking of the skin and failure of
the horizontal stabilizer.
The manufacturer’s service
information states that in addition to
cracks, the horizontal stabilizer may
VerDate Aug<31>2005
17:21 Mar 06, 2008
Jkt 214001
have deformation or debonding around
and between the inserts. The proposed
AD would require actions that are
intended to address all these unsafe
conditions.
You may obtain further information
by examining the MCAI and service
information in the AD docket.
Relevant Service Information
Transport Canada has issued Alert
Service Bulletins 206L–06–141 and
407–06–72, both dated September 12,
2006. The actions described in the
MCAI are intended to correct the same
unsafe condition as that identified in
the service information.
FAA’s Determination and Proposed
Requirements
This product has been approved by
the aviation authority of Canada and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with this State of Design
Authority, we have been notified of the
unsafe condition described in the MCAI
and service information. We are
proposing this AD because we evaluated
all pertinent information and
determined an unsafe condition exists
and is likely to exist or develop on other
products of these same type designs.
Differences Between This AD and the
MCAI
We have reviewed the MCAI and
related service information and, in
general, agree with their substance.
However, we have changed the alternate
compliance time from May 9, 2007, to
within 30 days, and we have not
mandated replacing the horizontal
stabilizer by a certain date. In making
this change, we do not intend to differ
substantively from the information
provided in the MCAI.
Differences are highlighted in the
‘‘Differences Between the FAA AD and
the MCAI’’ section in the proposed AD.
Costs of Compliance
We estimate that this proposed AD
would affect 59 horizontal stabilizers
(27–206L and 32–407 models) on about
1156 products of U.S. registry. We also
estimate that it would take about:
• 2.5 work hours to determine if the
affected part is installed on the
helicopter,
• 4 work hours to perform the initial
and 600-hour recurring inspection, and
• 8 work hours to remove and replace
an affected part.
• The average labor rate is $80 per
work-hour.
• Required parts would cost about
$20,173 for the Model 206L series and
$25,669 for the Model 407 helicopters.
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Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators would be $1,663,519,
assuming operators of the entire fleet
would need to determine whether they
have an affected part installed; the 59
helicopters with the affected parts
would undergo the initial inspection; 30
helicopters with the affected part would
undergo one recurring 600-hour
inspection; and all 59 affected parts
would be replaced.
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 above, 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); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules
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 AD:
Bell Helicopter Textron Canada: Docket No.
FAA–2008–0258; Directorate Identifier 2007–
SW–22–AD.
Comments Due Date
(a) We must receive comments by April 7,
2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Models 206L, 206L–
1, 206L–3, and 206L–4 with horizontal
stabilizer, part number (P/N) 206–023–119–
167, and Model 407 with horizontal
stabilizer, P/N 407–023–801–109, installed,
certificated in any category.
rwilkins on PROD1PC63 with PROPOSALS
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states:
Horizontal stabilizers part numbers 206–
023–119–167 and 407–023–801–109 may
have manufacturing flaws on the inside
surface of the upper and/or lower skin at the
tailboom attachment inserts. These flaws may
result in cracking of the skin and failure of
the horizontal stabilizer.
The manufacturer’s service information
states that in addition to cracks, the
horizontal stabilizer may have deformation or
debonding around and between the inserts.
The proposed AD would require actions that
are intended to address all these unsafe
conditions.
Actions and Compliance
(e) Within the next 100 hours time-inservice (TIS) or 30 days, whichever occurs
first, unless done previously.
(1) Determine whether you have an
affected serial numbered horizontal stabilizer
installed by removing the elevators from the
horizontal stabilizer. Access the horizontal
stabilizer identification tag containing the
horizontal stabilizer serial number as shown
in Figure 1 and remove the elevators by
following the Accomplishment Instructions,
Part I, of Bell Helicopter Textron Canada
(BHTC) Alert Service Bulletin (ASB) No.
206L–06–141, dated September 12, 2006,
applicable to the Model 206L series
helicopter (206L ASB) or BHTC ASB No.
407–06–72, dated September 12, 2006,
applicable to the Model 407 helicopters (407
ASB).
(2) If the serial number on the
identification tag is a serial number listed in
VerDate Aug<31>2005
17:21 Mar 06, 2008
Jkt 214001
Table 1 of the 206L ASB or 407 ASB, inspect
the horizontal stabilizer as follows:
(i) Using a 10x or higher magnifying glass,
inspect the horizontal stabilizer for a crack or
deformation around the areas of the inserts.
Also, using a tap test method, inspect for
debonding between the inserts by following
the Accomplishment Instructions, Part II, of
either the 206L ASB or 407 ASB, as
applicable.
(ii) If you find a crack, deformation, or
debonding, replace the horizontal stabilizer
with an airworthy horizontal stabilizer that
does not have a serial number listed in Table
1 of the 206L ASB or 407 ASB. Replace the
horizontal stabilizer by following the
Accomplishment Instructions, Part III, of
either the 206L ASB or the 407 ASB, as
applicable.
(iii) If you do not find a crack, deformation,
or debonding, thereafter, at intervals not to
exceed 600 hours TIS or during each annual
inspection, whichever occurs first, repeat the
inspection required by paragraph (e)(2)(i) of
this AD.
(f) Replacing any horizontal stabilizer
containing a serial number listed in Table 1
of 206L ASB or 407 ASB with a horizontal
stabilizer that does not contain such a serial
number by following the Accomplishment
Instructions, Part III, of either the 206L ASB
or 407 ASB, as applicable, constitutes
terminating actions for the requirements of
this AD.
Differences Between the FAA AD and the
MCAI
(g) The MCAI requires compliance ‘‘within
the next 100 hours air time but no later than
9 May 2007.’’ This AD requires compliance
within the next 100 hours TIS or 30 days,
whichever occurs first, unless done
previously. Also, the MCAI requires
replacing the horizontal stabilizer by
September 30, 2008, and we have not
mandated a compliance time for replacing
the horizontal stabilizer.
Subject
(h) Air Transport Association of America
(ATA) Code: 5510 Horizontal Stabilizer
Structure.
Other Information
(i) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN Sharon Miles, Aviation
Safety Engineer, FAA, Rotorcraft Directorate,
Regulations and Guidance Group, Fort
Worth, Texas 76193–0111, telephone (817)
222–5122, fax (817) 222–5961.
(2) Airworthy Product: Use only FAAapproved corrective actions. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent) if the State of
Design has an appropriate bilateral agreement
with the United States. You are required to
assure the product is airworthy before it is
returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
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12305
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(j) MCAI Transport Canada Airworthiness
Directive No. CF–2007–03, dated March 27,
2007, contain related information.
Issued in Fort Worth, Texas, on February
28, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–4495 Filed 3–6–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
National Institute of Standards and
Technology
15 CFR Part 296
[Docket No: 071106659–7661–01]
RIN 0693–AB59
Technology Innovation Program
National Institute of Standards
and Technology, United States
Department of Commerce.
ACTION: Notice of proposed rulemaking;
request for comments.
AGENCY:
SUMMARY: The Director of the National
Institute of Standards and Technology
(NIST), United States Department of
Commerce, requests comments on
proposed regulations which implement
the Technology Innovation Program
(TIP). The proposed rule prescribes
policies and procedures for the award of
financial assistance (grants and/or
cooperative agreements) under TIP. In
addition, NIST is revising the heading of
Subchapter K of its regulations to
accurately reflect the current contents of
that subchapter.
DATES: Comments must be received no
later than April 21, 2008.
ADDRESSES: Comments on the proposed
regulations must be submitted in
writing to: National Institute of
Standards and Technology, Technology
Innovation Program NPRM, 100 Bureau
Drive, Mail Stop 4700, Gaithersburg,
MD 20899–4700, or via the Federal eRulemaking Portal:
www.regulations.gov. Follow the
instructions for submitting comments.
FOR FURTHER INFORMATION CONTACT:
Barbara Lambis via e-mail at
barbara.lambis@nist.gov or telephone
(301) 975–4447.
SUPPLEMENTARY INFORMATION: The
America Creating Opportunities to
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]]>Agencies
[Federal Register Volume 73, Number 46 (Friday, March 7, 2008)]
[Proposed Rules]
[Pages 12303-12305]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4495]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0258; Directorate Identifier 2007-SW-22-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Models
206L, L-1, L-3, L-4, and 407 Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
specified Bell Helicopter Textron Canada (BHTC) helicopters. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
Aviation Authority of Canada with whom we have a bilateral agreement
states in the MCAI:
Horizontal stabilizers part numbers 206-023-119-167 and 407-023-
801-109 may have manufacturing flaws on the inside surface of the
upper and/or lower skin at the tailboom attachment inserts. These
flaws may result in cracking of the skin and failure of the
horizontal stabilizer.
The manufacturer's service information states that in addition to
cracks, the horizontal stabilizer may have deformation or debonding
around and between the inserts. The proposed AD would require actions
that are intended to address all these unsafe conditions.
DATES: We must receive comments on this proposed AD by April 7, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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 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 FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
[[Page 12304]]
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0258;
Directorate Identifier 2007-SW-22-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Transport Canada, which is the aviation authority for Canada, has
issued an MCAI in the form of Canadian Airworthiness Directive No. CF-
2007-03, dated March 27, 2007 (referred to after this as ``the MCAI''),
to correct an unsafe condition for these Canadian-certificated
products. The MCAI states:
Horizontal stabilizers part numbers 206-023-119-167 and 407-023-
801-109 may have manufacturing flaws on the inside surface of the
upper and/or lower skin at the tailboom attachment inserts. These
flaws may result in cracking of the skin and failure of the
horizontal stabilizer.
The manufacturer's service information states that in addition to
cracks, the horizontal stabilizer may have deformation or debonding
around and between the inserts. The proposed AD would require actions
that are intended to address all these unsafe conditions.
You may obtain further information by examining the MCAI and
service information in the AD docket.
Relevant Service Information
Transport Canada has issued Alert Service Bulletins 206L-06-141 and
407-06-72, both dated September 12, 2006. The actions described in the
MCAI are intended to correct the same unsafe condition as that
identified in the service information.
FAA's Determination and Proposed Requirements
This product has been approved by the aviation authority of Canada
and is approved for operation in the United States. Pursuant to our
bilateral agreement with this State of Design Authority, we have been
notified of the unsafe condition described in the MCAI and service
information. We are proposing this AD because we evaluated all
pertinent information and determined an unsafe condition exists and is
likely to exist or develop on other products of these same type
designs.
Differences Between This AD and the MCAI
We have reviewed the MCAI and related service information and, in
general, agree with their substance. However, we have changed the
alternate compliance time from May 9, 2007, to within 30 days, and we
have not mandated replacing the horizontal stabilizer by a certain
date. In making this change, we do not intend to differ substantively
from the information provided in the MCAI.
Differences are highlighted in the ``Differences Between the FAA AD
and the MCAI'' section in the proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 59 horizontal
stabilizers (27-206L and 32-407 models) on about 1156 products of U.S.
registry. We also estimate that it would take about:
2.5 work hours to determine if the affected part is
installed on the helicopter,
4 work hours to perform the initial and 600-hour recurring
inspection, and
8 work hours to remove and replace an affected part.
The average labor rate is $80 per work-hour.
Required parts would cost about $20,173 for the Model 206L
series and $25,669 for the Model 407 helicopters.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators would be $1,663,519, assuming operators of the entire
fleet would need to determine whether they have an affected part
installed; the 59 helicopters with the affected parts would undergo the
initial inspection; 30 helicopters with the affected part would undergo
one recurring 600-hour inspection; and all 59 affected parts would be
replaced.
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 above, 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); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 12305]]
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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Bell Helicopter Textron Canada: Docket No. FAA-2008-0258;
Directorate Identifier 2007-SW-22-AD.
Comments Due Date
(a) We must receive comments by April 7, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Models 206L, 206L-1, 206L-3, and 206L-4
with horizontal stabilizer, part number (P/N) 206-023-119-167, and
Model 407 with horizontal stabilizer, P/N 407-023-801-109,
installed, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states:
Horizontal stabilizers part numbers 206-023-119-167 and 407-023-
801-109 may have manufacturing flaws on the inside surface of the
upper and/or lower skin at the tailboom attachment inserts. These
flaws may result in cracking of the skin and failure of the
horizontal stabilizer.
The manufacturer's service information states that in addition
to cracks, the horizontal stabilizer may have deformation or
debonding around and between the inserts. The proposed AD would
require actions that are intended to address all these unsafe
conditions.
Actions and Compliance
(e) Within the next 100 hours time-in-service (TIS) or 30 days,
whichever occurs first, unless done previously.
(1) Determine whether you have an affected serial numbered
horizontal stabilizer installed by removing the elevators from the
horizontal stabilizer. Access the horizontal stabilizer
identification tag containing the horizontal stabilizer serial
number as shown in Figure 1 and remove the elevators by following
the Accomplishment Instructions, Part I, of Bell Helicopter Textron
Canada (BHTC) Alert Service Bulletin (ASB) No. 206L-06-141, dated
September 12, 2006, applicable to the Model 206L series helicopter
(206L ASB) or BHTC ASB No. 407-06-72, dated September 12, 2006,
applicable to the Model 407 helicopters (407 ASB).
(2) If the serial number on the identification tag is a serial
number listed in Table 1 of the 206L ASB or 407 ASB, inspect the
horizontal stabilizer as follows:
(i) Using a 10x or higher magnifying glass, inspect the
horizontal stabilizer for a crack or deformation around the areas of
the inserts. Also, using a tap test method, inspect for debonding
between the inserts by following the Accomplishment Instructions,
Part II, of either the 206L ASB or 407 ASB, as applicable.
(ii) If you find a crack, deformation, or debonding, replace the
horizontal stabilizer with an airworthy horizontal stabilizer that
does not have a serial number listed in Table 1 of the 206L ASB or
407 ASB. Replace the horizontal stabilizer by following the
Accomplishment Instructions, Part III, of either the 206L ASB or the
407 ASB, as applicable.
(iii) If you do not find a crack, deformation, or debonding,
thereafter, at intervals not to exceed 600 hours TIS or during each
annual inspection, whichever occurs first, repeat the inspection
required by paragraph (e)(2)(i) of this AD.
(f) Replacing any horizontal stabilizer containing a serial
number listed in Table 1 of 206L ASB or 407 ASB with a horizontal
stabilizer that does not contain such a serial number by following
the Accomplishment Instructions, Part III, of either the 206L ASB or
407 ASB, as applicable, constitutes terminating actions for the
requirements of this AD.
Differences Between the FAA AD and the MCAI
(g) The MCAI requires compliance ``within the next 100 hours air
time but no later than 9 May 2007.'' This AD requires compliance
within the next 100 hours TIS or 30 days, whichever occurs first,
unless done previously. Also, the MCAI requires replacing the
horizontal stabilizer by September 30, 2008, and we have not
mandated a compliance time for replacing the horizontal stabilizer.
Subject
(h) Air Transport Association of America (ATA) Code: 5510
Horizontal Stabilizer Structure.
Other Information
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Send information to ATTN Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
(2) Airworthy Product: Use only FAA-approved corrective actions.
Corrective actions are considered FAA-approved if they are approved
by the State of Design Authority (or their delegated agent) if the
State of Design has an appropriate bilateral agreement with the
United States. You are required to assure the product is airworthy
before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(j) MCAI Transport Canada Airworthiness Directive No. CF-2007-
03, dated March 27, 2007, contain related information.
Issued in Fort Worth, Texas, on February 28, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-4495 Filed 3-6-08; 8:45 am]
BILLING CODE 4910-13-P
