Airworthiness Directives; Air Tractor, Inc., Models AT-402, AT-402A, and AT-402B Airplanes, 38933-38935 [E8-15456]
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<![CDATA[
38933
Proposed Rules
Federal Register
Vol. 73, No. 131
Tuesday, July 8, 2008
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0749; Directorate
Identifier 2008–CE–044–AD]
RIN 2120–AA64
Airworthiness Directives; Air Tractor,
Inc., Models AT–402, AT–402A, and
AT–402B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
ebenthall on PRODPC60 with PROPOSALS
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Air Tractor, Inc., (Air Tractor) Models
AT–402, AT–402A, and AT–402B
airplanes. This proposed AD would
require you to repetitively visually
inspect the rudder and vertical fin hinge
attaching structure for loose fasteners
and inspect the rudder or vertical fin
skins, spars, hinges or brackets for
cracks and/or corrosion. The AD would
also require you to replace any damaged
parts found as a result of the inspections
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 a report of a
Model AT–402 airplane with a loose
upper rudder hinge caused by fatigue.
We are proposing this AD to detect and
correct loose fasteners; any cracks in the
rudder or vertical fin skins, spars,
hinges or brackets; or corrosion of the
rudder and vertical fin hinge attaching
structure. Hinge failure adversely affects
ability to control yaw and has led to the
rudder folding over in flight. This
condition could allow the rudder to
contact the elevator and affect ability to
control pitch with consequent loss of
control.
DATES: We must receive comments on
this proposed AD by September 8, 2008.
VerDate Aug<31>2005
14:18 Jul 07, 2008
Jkt 214001
Use one of the following
addresses to comment on this proposed
AD:
• 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.
For service information identified in
this proposed AD, contact Air Tractor,
Inc., P.O. Box 485, Olney, Texas 76374;
telephone: (940) 564–5616; facsimile:
(940) 564–5612.
FOR FURTHER INFORMATION CONTACT:
Andrew McAnaul, Aerospace Engineer,
ASW–150 (c/o MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308–
3365; facsimile: (210) 308–3370.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2008–0749; Directorate
Identifier 2008–CE–044–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 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://
www.regulations.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
We received two reports (one Air
Tractor Model AT–602 airplane and one
Model AT–802A airplane) of in-flight
rudder separation at the upper attach
hinge area and other reports of Models
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
AT–502B, AT–602, and AT–802/802A
airplanes with loose hinges, skin cracks,
or signs of repairs to the affected area.
Hinge failure adversely affects ability
to control yaw and has led to the rudder
folding over in flight. This condition
could allow the rudder to contact the
elevator and affect ability to control
pitch with consequent loss of control.
Consequently, we issued AD 2006–
23–14 (71 FR 66661, November 16,
2006). AD 2006–23–14 requires you to
repetitively visually inspect the rudder
and vertical fin hinge attaching
structure (vertical fin skins, spars,
hinges, and brackets) for loose fasteners,
cracks, and/or corrosion. This AD also
requires you to replace any damaged
parts found as a result of the inspection
and install an external doubler at the
upper rudder hinge.
Since issuing AD 2006–23–14, we
have received a report of a Model AT–
402 airplane with a loose upper rudder
hinge caused by fatigue. Therefore, we
are proposing this AD to address the
unsafe condition on the Model AT–402
airplanes.
Relevant Service Information
We have reviewed Snow Engineering
Co. Service Letter #247, revised June 2,
2008; and Snow Engineering Co. Process
Specification Number 145, dated
December 6, 1991. The service
information describes procedures for:
• Inspecting (visually) the rudder and
fin hinge attaching structure for loose
fasteners, any cracks in the rudder or
vertical fin skins, spars, hinges or
brackets, or corrosion;
• Replacing any damaged parts found
as a result of the inspection;
• Installing an external doubler at the
upper rudder hinge; and
• Balancing of the rudder.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. 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. This proposed AD would also
require you to replace any damaged
parts found as a result of the inspection
E:\FR\FM\08JYP1.SGM
08JYP1
38934
Federal Register / Vol. 73, No. 131 / Tuesday, July 8, 2008 / Proposed Rules
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.
Costs of Compliance
We estimate that this proposed AD
would affect 220 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
1 work-hour × $80 per hour = $80 ............................................................
Not applicable ..................................
$80
$17,600
Any required repairs will vary
depending upon the damage found, and
any replacements required will vary
based on the results of the inspection.
Based on this, we have no way of
determining the potential repair and/or
replacement costs for each airplane or
the number of airplanes that will need
the repairs and/or replacements based
on the result of the inspections.
We estimate the following costs to do
the proposed installation of the external
doubler at the upper rudder hinge:
Labor cost
Parts cost
Total cost per
airplane
5 work-hours × $80 per hour = $400 ......................................................................................................................
$217
$617
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.
ebenthall on PRODPC60 with PROPOSALS
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;
VerDate Aug<31>2005
14:18 Jul 07, 2008
Jkt 214001
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://www.regulations.gov;
or in person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5527) 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 FAA proposes to amend 14 CFR part
39 as follows:
1. The authority citation for part 39
continues to read as follows:
Frm 00002
Fmt 4702
Sfmt 4702
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Air Tractor, Inc.: Docket No. FAA–2008–
0749; Directorate Identifier 2008–CE–
044–AD.
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by
September 8, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models AT–402,
AT–402A, and AT–402B airplanes, serial
numbers 0694 through 1176, that are
certificated in any category.
Unsafe Condition
(d) This AD results from a report of a
Model AT–402 airplane with a loose upper
rudder hinge caused by fatigue. We are
issuing this AD to detect and correct loose
fasteners; any cracks in the rudder or vertical
fin skins, spars, hinges or brackets; or
corrosion of the rudder and vertical fin hinge
attaching structure. Hinge failure adversely
affects ability to control yaw and has led to
the rudder folding over in flight. This
condition could allow the rudder to contact
the elevator and affect ability to control pitch
with consequent loss of control.
Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
PO 00000
Authority: 49 U.S.C. 106(g), 40113, 44701.
(e) To address this problem, you must do
the following, unless already done:
E:\FR\FM\08JYP1.SGM
08JYP1
Federal Register / Vol. 73, No. 131 / Tuesday, July 8, 2008 / Proposed Rules
38935
Actions
Compliance
Procedures
(1) Inspect visually the rudder and vertical fin
hinge attachment for loose fasteners; and inspect the rudder or vertical fin skins, spars,
hinges or brackets for cracks and/or corrosion.
Initially inspect when the airplane reaches a
total of 3,500 hours time-in-service (TIS) or
within the next 100 hours TIS after the effective date of this AD, whichever occurs
later, unless already done. Thereafter, repetitively inspect at intervals not to exceed
every 100 hours TIS. Installation of the external doubler at the upper rudder hinge required by paragraph (e)(2)(ii) or (e)(3) of
this AD is terminating action for the repetitive inspections required by this AD.
Before further flight after any inspection required by paragraph (e)(1) of this AD where
you find any damaged parts. The installation of the external doubler at the upper
rudder hinge required by paragraph (e)(2)(ii)
or (e)(3) of this AD terminates the action for
the repetitive inspections required by this
AD.
When the airplane reaches a total of 5,000
hours TIS after the effective date of this AD
or within the next 100 hours TIS after the
effective date of this AD, whichever occurs
later, unless already done. The installation
of the external doubler at the upper rudder
hinge required by paragraph (e)(2)(ii) or
(e)(3) of this AD terminates the action for
the repetitive inspections required by this
AD.
As of the effective date of this AD ...................
Follow Snow Engineering Co. Service Letter
#247, revised June 2, 2008.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Fort Worth Aircraft
Certification Office, 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: Andrew
McAnaul, Aerospace Engineer, ASW–150
(c/o MIDO–43), 10100 Reunion Place, Suite
650, San Antonio, Texas 78216; telephone:
(210) 308–3365; facsimile: (210) 308–3370.
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.
Federal Aviation Administration
This condition, if not corrected, causes
mechanical interference which could result
in a situation where, during emergency
procedures, the landing gear cannot be
extended.
(2) If you find any damage as a result of any
inspection required by paragraph (e)(1) of
this AD, you must:
(i) Replace any damaged parts with new
parts and
(ii) Do the installation of the external doubler at the upper rudder hinge.
(3) Do the installation of the external doubler at
the upper rudder hinge.
(4) Do not install any rudder without the external doubler at the upper rudder hinge required by paragraph (e)(3) of this AD.
Related Information
ebenthall on PRODPC60 with PROPOSALS
(g) To get copies of the service information
referenced in this AD, contact Air Tractor,
Inc., P.O. Box 485, Olney, Texas 76374;
telephone: (940) 564–5616; facsimile: (940)
564–5612. To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590, or on
the Internet at https://www.regulations.gov.
Issued in Kansas City, Missouri, on July 1,
2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–15456 Filed 7–7–08; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
14:18 Jul 07, 2008
Jkt 214001
14 CFR Part 39
[Docket No. FAA–2008–0748; Directorate
Identifier 2008–CE–041–AD]
RIN 2120–AA64
Airworthiness Directives; EADS
SOCATA Model TBM 700 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 the
products listed above. 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 MCAI describes the unsafe
condition as:
It has been discovered that a risk of
mechanical interference exists in the
movement of the emergency landing gear bypass selector, due to an insufficient
functional gap between a floor panel
attachment lug and the landing gear control
button.
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
Follow Snow Engineering Co. Service Letter
#247, revised June 2, 2008; and Snow Engineering Co. Process Specification Number
145, dated December 6, 1991.
Follow Snow Engineering Co. Service Letter
#247, revised June 2, 2008; and Snow Engineering Co. Process Specification Number
145, dated December 6, 1991.
Not Applicable.
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by August 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 Management Facility between 9
a.m. and 5 p.m., Monday through
E:\FR\FM\08JYP1.SGM
08JYP1
]]>Agencies
[Federal Register Volume 73, Number 131 (Tuesday, July 8, 2008)]
[Proposed Rules]
[Pages 38933-38935]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15456]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 73, No. 131 / Tuesday, July 8, 2008 /
Proposed Rules
[[Page 38933]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0749; Directorate Identifier 2008-CE-044-AD]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc., Models AT-402, AT-
402A, and AT-402B 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
certain Air Tractor, Inc., (Air Tractor) Models AT-402, AT-402A, and
AT-402B airplanes. This proposed AD would require you to repetitively
visually inspect the rudder and vertical fin hinge attaching structure
for loose fasteners and inspect the rudder or vertical fin skins,
spars, hinges or brackets for cracks and/or corrosion. The AD would
also require you to replace any damaged parts found as a result of the
inspections 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 a report of a Model AT-402 airplane with a
loose upper rudder hinge caused by fatigue. We are proposing this AD to
detect and correct loose fasteners; any cracks in the rudder or
vertical fin skins, spars, hinges or brackets; or corrosion of the
rudder and vertical fin hinge attaching structure. Hinge failure
adversely affects ability to control yaw and has led to the rudder
folding over in flight. This condition could allow the rudder to
contact the elevator and affect ability to control pitch with
consequent loss of control.
DATES: We must receive comments on this proposed AD by September 8,
2008.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
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.
For service information identified in this proposed AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-
5616; facsimile: (940) 564-5612.
FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2008-0749; Directorate Identifier 2008-CE-044-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 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://
www.regulations.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
We received two reports (one Air Tractor Model AT-602 airplane and
one Model AT-802A airplane) of in-flight rudder separation 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.
Hinge failure adversely affects ability to control yaw and has led
to the rudder folding over in flight. This condition could allow the
rudder to contact the elevator and affect ability to control pitch with
consequent loss of control.
Consequently, we issued AD 2006-23-14 (71 FR 66661, November 16,
2006). AD 2006-23-14 requires you to repetitively visually inspect the
rudder and vertical fin hinge attaching structure (vertical fin skins,
spars, hinges, and brackets) for loose fasteners, cracks, and/or
corrosion. This AD also requires you to replace any damaged parts found
as a result of the inspection and install an external doubler at the
upper rudder hinge.
Since issuing AD 2006-23-14, we have received a report of a Model
AT-402 airplane with a loose upper rudder hinge caused by fatigue.
Therefore, we are proposing this AD to address the unsafe condition on
the Model AT-402 airplanes.
Relevant Service Information
We have reviewed Snow Engineering Co. Service Letter 247,
revised June 2, 2008; and Snow Engineering Co. Process Specification
Number 145, dated December 6, 1991. The service information describes
procedures for:
Inspecting (visually) the rudder and fin hinge attaching
structure for loose fasteners, any cracks in the rudder or vertical fin
skins, spars, hinges or brackets, or corrosion;
Replacing any damaged parts found as a result of the
inspection;
Installing an external doubler at the upper rudder hinge;
and
Balancing of the rudder.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. 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. This proposed AD would also require you to replace any
damaged parts found as a result of the inspection
[[Page 38934]]
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.
Costs of Compliance
We estimate that this proposed AD would affect 220 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80............. Not applicable................. $80 $17,600
----------------------------------------------------------------------------------------------------------------
Any required repairs will vary depending upon the damage found, and
any replacements required will vary based on the results of the
inspection. Based on this, we have no way of determining the potential
repair and/or replacement costs for each airplane or the number of
airplanes that will need the repairs and/or replacements based on the
result of the inspections.
We estimate the following costs to do the proposed installation of
the external doubler at the upper rudder hinge:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
5 work-hours x $80 per hour = $400.... $217 $617
------------------------------------------------------------------------
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 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://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
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 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:
Air Tractor, Inc.: Docket No. FAA-2008-0749; Directorate Identifier
2008-CE-044-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by September 8, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models AT-402, AT-402A, and AT-402B
airplanes, serial numbers 0694 through 1176, that are certificated
in any category.
Unsafe Condition
(d) This AD results from a report of a Model AT-402 airplane
with a loose upper rudder hinge caused by fatigue. We are issuing
this AD to detect and correct loose fasteners; any cracks in the
rudder or vertical fin skins, spars, hinges or brackets; or
corrosion of the rudder and vertical fin hinge attaching structure.
Hinge failure adversely affects ability to control yaw and has led
to the rudder folding over in flight. This condition could allow the
rudder to contact the elevator and affect ability to control pitch
with consequent loss of control.
Compliance
(e) To address this problem, you must do the following, unless
already done:
[[Page 38935]]
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect visually the rudder Initially inspect Follow Snow
and vertical fin hinge when the airplane Engineering Co.
attachment for loose fasteners; reaches a total Service Letter
and inspect the rudder or of 3,500 hours 247,
vertical fin skins, spars, time-in-service revised June 2,
hinges or brackets for cracks (TIS) or within 2008.
and/or corrosion. the next 100
hours TIS after
the effective
date of this AD,
whichever occurs
later, unless
already done.
Thereafter,
repetitively
inspect at
intervals not to
exceed every 100
hours TIS.
Installation of
the external
doubler at the
upper rudder
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
is terminating
action for the
repetitive
inspections
required by this
AD.
(2) If you find any damage as a Before further Follow Snow
result of any inspection flight after any Engineering Co.
required by paragraph (e)(1) of inspection Service Letter
this AD, you must: required by 247,
(i) Replace any damaged parts paragraph (e)(1) revised June 2,
with new parts and. of this AD where 2008; and Snow
(ii) Do the installation of the you find any Engineering Co.
external doubler at the upper damaged parts. Process
rudder hinge.. The installation Specification
of the external Number 145, dated
doubler at the December 6, 1991.
upper rudder
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
terminates the
action for the
repetitive
inspections
required by this
AD.
(3) Do the installation of the When the airplane Follow Snow
external doubler at the upper reaches a total Engineering Co.
rudder hinge. of 5,000 hours Service Letter
TIS after the 247,
effective date of revised June 2,
this AD or within 2008; and Snow
the next 100 Engineering Co.
hours TIS after Process
the effective Specification
date of this AD, Number 145, dated
whichever occurs December 6, 1991.
later, unless
already done. The
installation of
the external
doubler at the
upper rudder
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
terminates the
action for the
repetitive
inspections
required by this
AD.
(4) Do not install any rudder As of the Not Applicable.
without the external doubler at effective date of
the upper rudder hinge required this AD.
by paragraph (e)(3) of this AD.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Aircraft Certification Office, 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:
Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100
Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210)
308-3365; facsimile: (210) 308-3370. 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.
Related Information
(g) To get copies of the service information referenced in this
AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374;
telephone: (940) 564-5616; facsimile: (940) 564-5612. To view the AD
docket, go to U.S. Department of Transportation, Docket Operations,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey
Avenue, SE., Washington, DC 20590, or on the Internet at https://
www.regulations.gov.
Issued in Kansas City, Missouri, on July 1, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-15456 Filed 7-7-08; 8:45 am]
BILLING CODE 4910-13-P
