Airworthiness Directives; Air Tractor, Inc. Models AT-402, AT-402A, and AT-402B Airplanes, 61343-61346 [E8-24137]
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Federal Register / Vol. 73, No. 201 / Thursday, October 16, 2008 / Rules and Regulations
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle Aircraft
Certification Office (SACO), FAA, ATTN:
Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, SACO,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6501; fax
(425) 917–6590; 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.
Material Incorporated by Reference
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
Instructions of Boeing Special Attention
Service Bulletin 747–28–2260, dated March
13, 2008.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2008–21–06 Boeing: Amendment 39–15690.
Docket No. FAA–2008–0640; Directorate
Identifier 2008–NM–070–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective November 20, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
400, 747–400D, and 747–400F series
airplanes, certificated in any category; as
identified in Boeing Special Attention
Service Bulletin 747–28–2260, dated March
13, 2008.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent a fire or
explosion in the fuel tank and consequent
loss of the airplane.
(h) You must use Boeing Special Attention
Service Bulletin 747–28–2260, dated March
13, 2008, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at
the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on October
2, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–24130 Filed 10–15–08; 8:45 am]
BILLING CODE 4910–13–P
rwilkins on PROD1PC63 with NOTICES
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Installation
(f) Within 60 months after the effective
date of this AD, install an extension tube to
the existing pump discharge port of the
scavenge pump on the outboard side of the
center fuel tank in the main fuel tank #2, in
accordance with the Accomplishment
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61343
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0749; Directorate
Identifier 2008–CE–044–AD; Amendment
39–15692; AD 2008–21–08]
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: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Air Tractor, Inc. (Air Tractor) Models
AT–402, AT–402A, and AT–402B
airplanes. This AD requires 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. This AD also requires 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 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.
DATES: This AD becomes effective on
November 20, 2008.
On November 20, 2008, the Director
of the Federal Register approved the
incorporation by reference of Snow
Engineering Co. Service Letter #247,
revised June 2, 2008, listed in this AD.
As of December 21, 2006 (71 FR
66661, November 16, 2006), the Director
of the Federal Register approved the
incorporation by reference of Snow
Engineering Co. Process Specification
Number 145, dated December 6, 1991,
listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas
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61344
Federal Register / Vol. 73, No. 201 / Thursday, October 16, 2008 / Rules and Regulations
76374; telephone: (940) 564–5616;
facsimile: (940) 564–5612; E-mail:
parts@airtractor.com; Web site: https://
www.airtractor.com.
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. The docket
number is FAA–2008–0749; Directorate
Identifier 2008–CE–044–AD.
FOR FURTHER INFORMATION CONTACT:
Andy McAnaul, Aerospace Engineer,
10100 Reunion Pl, San Antonio, Texas
78216; telephone: (210) 308–3365; fax:
(210) 308–3370.
SUPPLEMENTARY INFORMATION:
Discussion
On July 1, 2008, we issued a proposal
to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to certain Air
Tractor Models AT–402, AT–402A, and
AT–402B airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on July 8, 2008 (73 FR 38933). The
NPRM proposed to 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. This 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.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 220
airplanes in the U.S. registry.
We estimate the following costs to do
the 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 replacements 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 replacement
costs for each airplane or the number of
airplanes that will need the
replacements based on the result of the
inspections.
We estimate the following costs to do
installation of the external doubler at
the upper rudder hinge:
Labor cost
Parts cost
Total cost
per airplane
Total cost
on U.S.
operators
5 work-hours × $80 per hour = $400 ......................................................................................................
$217
$617
$135,740
rwilkins on PROD1PC63 with NOTICES
Authority for This Rulemaking
Regulatory Findings
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 AD.
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under 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 summary of the costs
to comply with this AD (and other
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information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2008–0749;
Directorate Identifier 2008 CE–044–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
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Federal Register / Vol. 73, No. 201 / Thursday, October 16, 2008 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
Effective Date
(a) This AD becomes effective on
November 20, 2008.
1. The authority citation for part 39
continues to read as follows:
Affected ADs
(b) None.
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
2. FAA amends § 39.13 by adding the
following new AD:
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.
2008–21–08 Air Tractor, Inc.: Amendment
39–15692; Docket No. FAA–2008–0749;
Directorate Identifier 2008–CE–044–AD.
Unsafe Condition
(d) This AD results from a report of a
Model AT–402 airplane with a loose upper
§ 39.13
[Amended]
■
61345
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:
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, and 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 November 20, 2008 (the effective date of this AD),
whichever occurs later. 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.
Follow Snow Engineering Co. Service Letter
#247, revised June 2, 2008.
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 repetitive
inspections required by this AD.
When the airplane reaches a total of 5,000
hours TIS after November 20, 2008 (the effective date of this AD) or within the next
100 hours TIS after November 20, 2008
(the effective date of this AD), whichever
occurs later. 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 repetitive inspections required by this AD.
As of November 20, 2008 (the effective date
of this AD).
Follow Snow Engineering Co. Service Letter
#247, revised June 2, 2008; and Snow Engineering Co. Process Specification Number
145, dated December 6, 1991.
Material Incorporated by Reference
(3) For service information identified in
this AD, contact Air Tractor, Inc., P.O. Box
485, Olney, Texas 76374; telephone: (940)
564–5616; facsimile: (940) 564–5612; E-mail:
parts@airtractor.com; Web site: https://
www.airtractor.com.
(4) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(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.
rwilkins on PROD1PC63 with NOTICES
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Fort Worth Airplane
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
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.
VerDate Aug<31>2005
16:18 Oct 15, 2008
Jkt 217001
(g) You must use Snow Engineering Co.
Service Letter #247, revised June 2, 2008; and
Snow Engineering Co. Process Specification
Number 145, dated December 6, 1991, to do
the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Snow Engineering Co. Service Letter #247,
revised June 2, 2008, under 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) On December 21, 2006 (71 FR 66661,
November 16, 2006), the Director of the
Federal Register approved the incorporation
by reference of Snow Engineering Co. Process
Specification Number 145, dated December
6, 1991.
PO 00000
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Fmt 4700
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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.
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61346
Federal Register / Vol. 73, No. 201 / Thursday, October 16, 2008 / Rules and Regulations
Issued in Kansas City, Missouri.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8–24137 Filed 10–15–08; 8:45 am]
[Docket No. FAA–2008–1088; Directorate
Identifier 2008–NE–15–AD; Amendment 39–
15691; AD 2008–21–07]
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Dowty
Propellers R408 Series Propellers
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is the same as the mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Terry Fahr, Aerospace Engineer, Boston
Aircraft Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: terry.fahr@faa.gov;
telephone (781) 238–7155; fax (781)
238–7170.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
rwilkins on PROD1PC63 with NOTICES
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued 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:
Three in-service propellers have been
found to have blades which have lost
the bonded metallic leading edge guard.
If the leading edge guard comes off as
the propeller turns, it could cause
secondary damage to aircraft or injury to
personnel. For the reasons described
above, EASA issued Emergency AD
2007–0223–E to require repetitive
inspections of the blade Leading Edge
(L/E) guards for correct bonding until
they accumulate more than 1,200 flight
hours (FH) time in service.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI, which
could result in the loss of the bonded
metallic leading edge guard, and could
result in damage to the airplane or
injury to personnel.
DATES: This AD becomes effective
October 31, 2008.
We must receive comments on this
AD by November 17, 2008.
The Director of the Federal Register
approved the incorporation by reference
of Dowty Propellers Alert Service
Bulletin (ASB) D8400–61–A69, dated
August 15, 2007, and ASB D8400–61–
A69, Revision 1, dated September 18,
2007, listed in the AD as of October 31,
2008.
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16:18 Oct 15, 2008
Jkt 217001
ADDRESSES:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0223 R2,
dated October 26, 2007, (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Three in-service propellers have been
found to have blades which have lost the
bonded metallic leading edge guard. If the
leading edge guard comes off as the propeller
turns, it could cause secondary damage to
aircraft or injury to personnel.
For the reasons described above,
EASA issued Emergency AD 2007–
0223–E to require repetitive inspections
of the blade Leading Edge (L/E) guards
for correct bonding until they
accumulate more than 1,200 FH time in
service. Revision 1 of this AD was
issued to clarify the required
inspections and follow-up actions
depending on findings and to make
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Frm 00022
Fmt 4700
Sfmt 4700
reference to the latest Dowty Alert
Service Bulletin (ASB) revision.
This AD has been further revised for
clarification, specifying that blades repaired
at the tip are only allowed to continue up to
500 hours in service after repair. This
limitation was already in the Dowty ASB and
the Note is added to the AD to avoid the
impression that the AD does not require the
same limitation.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Dowty Propellers has issued Alert
Service Bulletins D8400–61–A69, dated
August 15, 2007; and Revision 1, dated
September 18, 2007. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of the United
Kingdom, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the United
Kingdom, they have notified us of the
unsafe condition described in the MCAI
and service information referenced
above. We are issuing this AD because
we evaluated all information provided
by the United Kingdom and determined
the unsafe condition exists and is likely
to exist or develop on other products of
the same type design.
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because the required compliance
time to detect the unsafe condition is
too short for public comment. Therefore,
we determined that notice and
opportunity for public comment before
issuing this AD are impracticable and
that good cause exists for making this
amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2008–1088;
Directorate Identifier 2008–NE–15–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
E:\FR\FM\16OCR1.SGM
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Agencies
[Federal Register Volume 73, Number 201 (Thursday, October 16, 2008)]
[Rules and Regulations]
[Pages 61343-61346]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-24137]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0749; Directorate Identifier 2008-CE-044-AD;
Amendment 39-15692; AD 2008-21-08]
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: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Air Tractor, Inc. (Air Tractor) Models AT-402, AT-402A, and AT-402B
airplanes. This AD requires 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. This AD also requires 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 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.
DATES: This AD becomes effective on November 20, 2008.
On November 20, 2008, the Director of the Federal Register approved
the incorporation by reference of Snow Engineering Co. Service Letter
247, revised June 2, 2008, listed in this AD.
As of December 21, 2006 (71 FR 66661, November 16, 2006), the
Director of the Federal Register approved the incorporation by
reference of Snow Engineering Co. Process Specification Number 145,
dated December 6, 1991, listed in this AD.
ADDRESSES: For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas
[[Page 61344]]
76374; telephone: (940) 564-5616; facsimile: (940) 564-5612; E-mail:
parts@airtractor.com; Web site: https://www.airtractor.com.
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. The docket number is FAA-2008-0749;
Directorate Identifier 2008-CE-044-AD.
FOR FURTHER INFORMATION CONTACT: Andy McAnaul, Aerospace Engineer,
10100 Reunion Pl, San Antonio, Texas 78216; telephone: (210) 308-3365;
fax: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Discussion
On July 1, 2008, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Air Tractor Models AT-402, AT-402A, and AT-402B
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on July 8, 2008 (73 FR 38933). The
NPRM proposed to 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. This 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.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 220 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost
Labor cost Parts cost Total cost on U.S.
per airplane operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80................ Not applicable.................... $80 $17,600
----------------------------------------------------------------------------------------------------------------
Any required replacements 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 replacement costs for each airplane or the number of
airplanes that will need the replacements based on the result of the
inspections.
We estimate the following costs to do installation of the external
doubler at the upper rudder hinge:
------------------------------------------------------------------------
Total cost
Labor cost Parts cost Total cost on U.S.
per airplane operators
------------------------------------------------------------------------
5 work-hours x $80 per hour = $217 $617 $135,740
$400.........................
------------------------------------------------------------------------
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 AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2008-0749; Directorate Identifier 2008 CE-044-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
[[Page 61345]]
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. FAA amends Sec. 39.13 by adding the following new AD:
2008-21-08 Air Tractor, Inc.: Amendment 39-15692; Docket No. FAA-
2008-0749; Directorate Identifier 2008-CE-044-AD.
Effective Date
(a) This AD becomes effective on November 20, 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:
------------------------------------------------------------------------
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, and brackets for cracks (TIS) or within 2008.
and/or corrosion. the next 100
hours TIS after
November 20, 2008
(the effective
date of this AD),
whichever occurs
later.
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
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 Before further Follow Snow
the external doubler at the flight after any Engineering Co.
upper rudder hinge. inspection Service Letter
required by 247,
paragraph (e)(1) revised June 2,
of this AD where 2008; and Snow
you find any Engineering Co.
damaged parts. Process
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
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 247,
November 20, 2008 revised June 2,
(the effective 2008; and Snow
date of this AD) Engineering Co.
or within the Process
next 100 hours Specification
TIS after Number 145, dated
November 20, 2008 December 6, 1991.
(the effective
date of this AD),
whichever occurs
later. 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
repetitive
inspections
required by this
AD.
(4) Do not install any rudder As of November 20, Not Applicable.
without the external doubler at 2008 (the
the upper rudder hinge required effective date of
by paragraph (e)(3) of this AD. this AD).
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Airplane Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. 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.
Material Incorporated by Reference
(g) You must use Snow Engineering Co. Service Letter
247, revised June 2, 2008; and Snow Engineering Co. Process
Specification Number 145, dated December 6, 1991, to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Snow Engineering Co. Service Letter
247, revised June 2, 2008, under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On December 21, 2006 (71 FR 66661, November 16, 2006), the
Director of the Federal Register approved the incorporation by
reference of Snow Engineering Co. Process Specification Number 145,
dated December 6, 1991.
(3) For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; facsimile: (940) 564-5612; E-mail: parts@airtractor.com;
Web site: https://www.airtractor.com.
(4) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.
[[Page 61346]]
Issued in Kansas City, Missouri.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8-24137 Filed 10-15-08; 8:45 am]
BILLING CODE 4910-13-P