Airworthiness Directives; Fuji Heavy Industries, Ltd. FA-200 Series Airplanes, 45449-45451 [E6-12953]
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<![CDATA[
Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
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.
Affected ADs
Regulatory Findings
Unsafe Condition
We have 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 that the 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 a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
(d) This AD results from a report of
electrical arcing of the essential bus feeder
cables behind hinged circuit breaker panel
CB3 P-K. We are issuing this AD to prevent
arcing of essential bus feeder cables due to
improper installation of the harness C112
clamp assembly, which could result in loss
of electrical systems and smoke and/or fire
behind the CB3 P-K hinged circuit breaker
panel in the flight compartment.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, 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.
jlentini on PROD1PC65 with PROPOSAL
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Lockheed: Docket No. FAA–2006–25554;
Directorate Identifier 2006–NM–123–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by September 25, 2006.
VerDate Aug<31>2005
18:06 Aug 08, 2006
Jkt 208001
(b) None.
Applicability
(c) This AD applies to Lockheed Model L–
1011–385–1, L–1011–385–1–14, L–1011–
385–1–15, and L–1011–385–3 series
airplanes, certificated in any category; having
serial numbers (S/N) 193A through 193Y
inclusive and 293A through 293F inclusive:
–1002 through –1250 inclusive.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2006–25259; Directorate
Identifier 2006–CE–36–AD]
RIN 2120–AA64
Airworthiness Directives; Fuji Heavy
Industries, Ltd. FA–200 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Detailed Inspection of the C112 Harness
Clamp Assembly
(f) Within 90 days after the effective date
of this AD: Do the actions in paragraphs (f)(1)
and (f)(2) of this AD by accomplishing all the
actions specified in the Accomplishment
Instructions of Lockheed L–1011 Service
Bulletin 093–24–142, dated November 16,
2005. Do all applicable corrective actions
before further flight.
(1) Perform a one-time detailed inspection
of the C112 harness clamp assembly to find
incorrectly installed harness clamps, and do
all applicable corrective actions.
(2) Perform a one-time detailed inspection
of the C112 and C162 harness assemblies to
find evidence of chafing, arcing, or
deterioration, and do all applicable corrective
actions.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Atlanta Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Frm 00013
Issued in Renton, Washington, on August
2, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–12948 Filed 8–8–06; 8:45 am]
Federal Aviation Administration
Compliance
PO 00000
45449
Fmt 4702
Sfmt 4702
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an airworthiness authority of
another country to identify and correct
an unsafe condition on an aviation
product. The proposed AD would
require actions that are intended to
address an unsafe condition described
in the MCAI.
DATES: We must receive comments on
this proposed AD by September 8, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand delivery: Room PL–401 on the
plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
the proposed AD, contact Fuji Heavy
Industries, Ltd., AEROSPACE
COMPANY, 1–11 YOUNAN 1 CHOME
UTSUNOMIYA TOCHIGI, JAPAN 320–
E:\FR\FM\09AUP1.SGM
09AUP1
45450
Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
8564; telephone: +81–28–684–7253;
facsimile: +81–28–684–7260.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, FAA, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. We are
prototyping this process and specifically
request your comments on its use. You
can find more information in FAA draft
Order 8040.2, ‘‘Airworthiness Directive
Process for Mandatory Continuing
Airworthiness Information’’ which is
currently open for comments at https://
www.faa.gov/aircraft/draft_docs. 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
existing AD issuance processes to meet
legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to
follow our technical decision-making
processes in all aspects to meet our
responsibilities to determine 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.
The comment period for this
proposed AD is open for 30 days to
allow time for comment on both the
process and the AD content. In the
future, ADs using this process will have
a 15-day comment period. The comment
period is reduced because the
airworthiness authority and
manufacturer have already published
the documents on which we based our
decision, making a longer comment
period unnecessary.
jlentini on PROD1PC65 with PROPOSAL
Comments Invited
We invite you to send any written
data, views, or arguments regarding this
proposed AD. Send your comments to
an address listed under the ADDRESSES
section. Include the docket number,
‘‘FAA–2006–25259; Directorate
Identifier 2006–CE–36–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
VerDate Aug<31>2005
18:06 Aug 08, 2006
Jkt 208001
environmental, and energy aspects of
the proposed AD. We are also inviting
comments, views, or arguments on the
new MCAI process. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
The Japan Civil Aviation Bureau,
which is the airworthiness authority for
Japan, has issued AD No. TCD–6832–
2006, Date of Issue: April 10, 2006
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states
that that the aircraft manufacturer has
identified field reports indicating
corrosion of the flanges of the main
wing spars. If not corrected, the
corrosion could cause deterioration of
wing strength. The MCAI requires
creation of inspection holes, corrosion
inspection of the flange of wing spar,
repair of corrosion if necessary and
removal of the sealing compound. You
may obtain further information by
examining the MCAI in the docket.
Relevant Service Information
Fuji Heavy Industries, Ltd. has issued
Service Bulletin No. 200–015, dated
February 28, 2006. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of the Proposed AD
This product is manufactured outside
the United States and is type certificated
for operation in the United States under
the provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
agreement. Pursuant to this bilateral
airworthiness agreement, the State of
Design’s airworthiness authority has
notified us of the unsafe condition
described in the MCAI and service
information referenced above. We have
examined the airworthiness authority’s
findings, evaluated all pertinent
information, and determined an unsafe
condition exists and is likely to exist or
develop on all products of this type
design. We are issuing this proposed AD
to correct the unsafe condition.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
Differences Between the Proposed AD
and the MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable in a U.S.
court of law. In making these changes,
we do not intend to differ substantively
from the information provided in the
MCAI and related service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
described in a separate paragraph of the
proposed AD. These proposed
requirements, if ultimately adopted, will
take precedence over the actions copied
from the MCAI.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 3 products of U.S. registry.
We also estimate that it would take
about 128 work-hours per product to do
the action and that the average labor rate
is $80 per work-hour. Required parts
would cost about $100 per product.
Where the service information lists
required parts costs that are covered
under warranty, we have assumed that
there will be no charge for these costs.
As we do not control warranty coverage
for affected parties, some parties may
incur costs higher than estimated here.
Based on these figures, we estimate the
cost of the proposed AD on U.S.
operators to be $31,020, or $10,340 per
product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies 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 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.
E:\FR\FM\09AUP1.SGM
09AUP1
Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
Regulatory Findings
We have 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 that the 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 a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
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:
jlentini on PROD1PC65 with PROPOSAL
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Fuji Heavy Industries, Ltd.: FAA–2006–
25259; Directorate Identifier 2006–CE–
36–AD.
VerDate Aug<31>2005
18:06 Aug 08, 2006
Jkt 208001
Comments Due Date
(a) We must receive comments on this
proposed airworthiness directive (AD) by
September 8, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all FA–200 series
airplanes, certificated in any U.S. category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states that
the aircraft manufacturer has identified field
reports indicating corrosion of the flanges of
the main wing spars. If not corrected, the
corrosion could cause deterioration of wing
strength. The MCAI requires creation of
inspection holes, corrosion inspection of the
flange of wing spar, repair of corrosion if
necessary and removal of the sealing
compound. You may obtain further
information by examining the MCAI in the
docket.
Actions and Compliance
(e) Unless already done, do the following
except as stated in paragraph (f) below.
(1) Within 1 year after the effective date of
this AD, carry out creation of inspection
holes, corrosion inspection of the flange of
wing spar, repair of corrosion if necessary
and removal of the sealing compound in
accordance with Fuji Heavy Industries, Ltd.
(FHI) Service Bulletin No. 200–015, dated
February 28, 2006 (SB).
(2) Within intervals not to exceed 5 years
from the previous inspection of paragraph
(e)(1) of this AD, carry out repetitive
corrosion inspection of the flange of wing
spar and repair of corrosion if necessary in
accordance with the SB.
FAA AD Differences
(f) The SB calls out contacting Fuji Heavy
Industries Ltd. for a structural integrity
evaluation if measured thickness exceeds
minimum allowable limits or if corrosion is
found on main spar flange in areas other than
fuel tank bay. Per paragraph (g)(2) of this AD,
any corrective action in this aspect or any
other aspect per this AD must be FAAapproved before returning the airplane to
service.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, ATTN: Doug Rudolph, Aerospace
Engineer, Small Airplane Directorate, FAA,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4059; facsimile:
(816) 329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) Return to Airworthiness: When
complying with this AD, perform FAAapproved corrective actions before returning
the product to an airworthy condition.
(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)
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
45451
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) This AD is related to Japan Civil
Aviation Bureau AD TCD–6832–2006, Date of
Issue: April 10, 2006, which references Fuji
Heavy Industries Ltd Service Bulletin No.
200–015, dated February 28, 2006.
Issued in Kansas City, Missouri, on August
3, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–12953 Filed 8–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25260; Directorate
Identifier 2006–CE–37–AD]
RIN 2120–AA64
Airworthiness Directives; Air Tractor,
Inc. Models AT–502, AT–502A, AT–
502B, AT–602, AT–802, and AT–802A
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Air Tractor, Inc. (Air Tractor) Models
AT–502, AT–502A, AT–502B, AT–602,
AT–802, and AT–802A airplanes. This
proposed AD would require you to
repetitively visually inspect the rudder
and vertical fin hinge attaching
structure for loose fasteners, any cracks
in the rudder or vertical fin skins, spars,
hinges or brackets, or corrosion. The AD
would also require you to replace any
damaged parts found as a result of the
inspection and install an external
doubler at the upper rudder hinge.
Installation of the external doubler at
the upper rudder hinge is terminating
action for the repetitive inspection
requirements. This proposed AD results
from two reports (one Model AT–602
airplane and one Model AT–802A
airplane) of in-flight rudder separation
from the vertical fin at the upper attach
hinge area, and other reports of Models
AT–502B, AT–602, and AT–802/802A
airplanes with loose hinges, skin cracks,
or signs of repairs to the affected area.
We are proposing this AD to detect and
correct loose fasteners; any cracks in the
rudder or vertical fin skins, spars,
E:\FR\FM\09AUP1.SGM
09AUP1
]]>Agencies
[Federal Register Volume 71, Number 153 (Wednesday, August 9, 2006)]
[Proposed Rules]
[Pages 45449-45451]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-12953]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25259; Directorate Identifier 2006-CE-36-AD]
RIN 2120-AA64
Airworthiness Directives; Fuji Heavy Industries, Ltd. FA-200
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an airworthiness
authority of another country to identify and correct an unsafe
condition on an aviation product. The proposed AD would require actions
that are intended to address an unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by September 8,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in the proposed AD, contact Fuji
Heavy Industries, Ltd., AEROSPACE COMPANY, 1-11 YOUNAN 1 CHOME
UTSUNOMIYA TOCHIGI, JAPAN 320-
[[Page 45450]]
8564; telephone: +81-28-684-7253; facsimile: +81-28-684-7260.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, FAA, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. We are prototyping this process and
specifically request your comments on its use. You can find more
information in FAA draft Order 8040.2, ``Airworthiness Directive
Process for Mandatory Continuing Airworthiness Information'' which is
currently open for comments at https://www.faa.gov/aircraft/draft_docs.
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 existing AD issuance processes
to meet legal, economic, Administrative Procedure Act, and Federal
Register requirements. We also continue to follow our technical
decision-making processes in all aspects to meet our responsibilities
to determine 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.
The comment period for this proposed AD is open for 30 days to
allow time for comment on both the process and the AD content. In the
future, ADs using this process will have a 15-day comment period. The
comment period is reduced because the airworthiness authority and
manufacturer have already published the documents on which we based our
decision, making a longer comment period unnecessary.
Comments Invited
We invite you to send any written data, views, or arguments
regarding this proposed AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number, ``FAA-2006-
25259; Directorate Identifier 2006-CE-36-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We are
also inviting comments, views, or arguments on the new MCAI process. We
will consider all comments received by the closing date and may amend
the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.
Discussion
The Japan Civil Aviation Bureau, which is the airworthiness
authority for Japan, has issued AD No. TCD-6832-2006, Date of Issue:
April 10, 2006 (referred to after this as ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states that that
the aircraft manufacturer has identified field reports indicating
corrosion of the flanges of the main wing spars. If not corrected, the
corrosion could cause deterioration of wing strength. The MCAI requires
creation of inspection holes, corrosion inspection of the flange of
wing spar, repair of corrosion if necessary and removal of the sealing
compound. You may obtain further information by examining the MCAI in
the docket.
Relevant Service Information
Fuji Heavy Industries, Ltd. has issued Service Bulletin No. 200-
015, dated February 28, 2006. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product is manufactured outside the United States and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral agreement. Pursuant to this bilateral
airworthiness agreement, the State of Design's airworthiness authority
has notified us of the unsafe condition described in the MCAI and
service information referenced above. We have examined the
airworthiness authority's findings, evaluated all pertinent
information, and determined an unsafe condition exists and is likely to
exist or develop on all products of this type design. We are issuing
this proposed AD to correct the unsafe condition.
Differences Between the Proposed AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable in a U.S. court of
law. In making these changes, we do not intend to differ substantively
from the information provided in the MCAI and related service
information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the proposed AD. These proposed
requirements, if ultimately adopted, will take precedence over the
actions copied from the MCAI.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 3 products of U.S. registry. We also estimate that
it would take about 128 work-hours per product to do the action and
that the average labor rate is $80 per work-hour. Required parts would
cost about $100 per product. Where the service information lists
required parts costs that are covered under warranty, we have assumed
that there will be no charge for these costs. As we do not control
warranty coverage for affected parties, some parties may incur costs
higher than estimated here. Based on these figures, we estimate the
cost of the proposed AD on U.S. operators to be $31,020, or $10,340 per
product.
Authority for This Rulemaking
Title 49 of the United States Code specifies 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 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.
[[Page 45451]]
Regulatory Findings
We have 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 that the 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 a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5227)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration 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:
Fuji Heavy Industries, Ltd.: FAA-2006-25259; Directorate Identifier
2006-CE-36-AD.
Comments Due Date
(a) We must receive comments on this proposed airworthiness
directive (AD) by September 8, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all FA-200 series airplanes, certificated
in any U.S. category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states that the aircraft manufacturer has identified field reports
indicating corrosion of the flanges of the main wing spars. If not
corrected, the corrosion could cause deterioration of wing strength.
The MCAI requires creation of inspection holes, corrosion inspection
of the flange of wing spar, repair of corrosion if necessary and
removal of the sealing compound. You may obtain further information
by examining the MCAI in the docket.
Actions and Compliance
(e) Unless already done, do the following except as stated in
paragraph (f) below.
(1) Within 1 year after the effective date of this AD, carry out
creation of inspection holes, corrosion inspection of the flange of
wing spar, repair of corrosion if necessary and removal of the
sealing compound in accordance with Fuji Heavy Industries, Ltd.
(FHI) Service Bulletin No. 200-015, dated February 28, 2006 (SB).
(2) Within intervals not to exceed 5 years from the previous
inspection of paragraph (e)(1) of this AD, carry out repetitive
corrosion inspection of the flange of wing spar and repair of
corrosion if necessary in accordance with the SB.
FAA AD Differences
(f) The SB calls out contacting Fuji Heavy Industries Ltd. for a
structural integrity evaluation if measured thickness exceeds
minimum allowable limits or if corrosion is found on main spar
flange in areas other than fuel tank bay. Per paragraph (g)(2) of
this AD, any corrective action in this aspect or any other aspect
per this AD must be FAA-approved before returning the airplane to
service.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, Small
Airplane Directorate, FAA, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-
4090, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
(2) Return to Airworthiness: When complying with this AD,
perform FAA-approved corrective actions before returning the product
to an airworthy condition.
(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
(h) This AD is related to Japan Civil Aviation Bureau AD TCD-
6832-2006, Date of Issue: April 10, 2006, which references Fuji
Heavy Industries Ltd Service Bulletin No. 200-015, dated February
28, 2006.
Issued in Kansas City, Missouri, on August 3, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-12953 Filed 8-8-06; 8:45 am]
BILLING CODE 4910-13-P
