Airworthiness Directives; Air Tractor, Inc. Models AT-502, AT-502A, AT-502B, AT-602, AT-802, and AT-802A Airplanes, 45451-45454 [E6-12940]
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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.
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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)
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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
45452
Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
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 of the airplane.
DATES: We must receive comments on
this proposed AD by October 10, 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–
0001.
• 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
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–2006–25260; Directorate
Identifier 2006–CE–37–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://
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
We have 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 of
the airplane.
Relevant Service Information
We have reviewed Snow Engineering
Co. Service Letter #247, dated August
14, 2005, revised May 17, 2006, 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 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.
Costs of Compliance
We estimate that this proposed AD
would affect 945 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
Total cost per
airplane
Labor cost
Parts cost
1 work-hour × $80 per hour = $80 ...............................
Not Applicable ..............................................................
We have no way of determining the
number of airplanes that may need any
replacements that would be required
based on the results of the proposed
inspection.
5 work-hours × $80 per hour = $400 ...........................
$217 ..............................................................................
jlentini on PROD1PC65 with PROPOSAL
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,
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$75,600
Total cost per
airplane
Parts cost
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
$80
We estimate the following costs to do
the installation of the external doubler
at the upper rudder hinge:
Labor cost
Authority for This Rulemaking
Total cost on
U.S. operators
Total cost on
U.S. operators
$617
$583,065
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
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Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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.
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,
Model
(1)
(2)
(3)
(4)
45453
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority : 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Air Tractor, Inc.: Docket No. FAA–2006–
25260; Directorate Identifier 2006–CE–
37–AD.
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by
October 10, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
Serial Nos.
AT–502 and AT–502B ........................................................................
AT–502A .............................................................................................
AT–602 ................................................................................................
AT–802 and AT–802A ........................................................................
Unsafe Condition
502/502B–0003 through 502/502B–2600.
502A–0003 through 502A–2582.
602–0337 through 602–1138.
802/802A–0001 through 802/802A–0215.
(d) This AD results from two reports (one
Model AT–602 airplane and one Model AT–
802A airplane) of in-flight rudder separations
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 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
of the airplane.
Actions
Compliance
Procedures
(1) Inspect visually the rudder and vertical
hinge attachment for loose fasteners; any
cracks in the rudder or vertical fin skins,
spars, hinges or brackets, or corrosion.
Initially inspect upon reaching 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 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 is the terminating action for
the repetitive inspections required by this
AD.
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006.
jlentini on PROD1PC65 with PROPOSAL
(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.
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Fmt 4702
Sfmt 4702
Compliance
(e) To address this problem, you must do
the following:
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006, and Snow Engineering Co. Process Specification Number 145, dated December 6, 1991.
E:\FR\FM\09AUP1.SGM
09AUP1
45454
Federal Register / Vol. 71, No. 153 / Wednesday, August 9, 2006 / Proposed Rules
Actions
Compliance
Procedures
(3) Do the installation of the external doubler at
the upper rudder hinge.
Upon accumulating 5,000 hours TIS 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 is the terminating action for the repetitive inspections required by this AD.
As of the effective date of this AD ...................
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006, and Snow Engineering Co. Process Specification Number 145, dated December 6, 1991.
Cessna Aircraft Company (Cessna)
Models 172R, 172S, 182S, 182T, T182T,
206H, and T206H airplanes. This
proposed AD would require you to
install Modification Kit MN172–25–10B
or a steel lock rod/bar on both crew seat
back cylinder lock assemblies. If a steel
lock rod/bar has already been installed
on the crew seat back cylinder lock
assembly, no further action is required.
If Modification Kit MK172–25–10A has
previously been installed, this proposed
AD would require you to do an
installation inspection and correct any
discrepancies found. This proposed AD
results from reports of the crew seat
back cylinder lock assembly failing at
the aft end and other cylinder lock
assemblies found cracked. We are
proposing this AD to prevent the crew
seat cylinder lock assembly from
bending, cracking, or failing. This
failure could cause uncontrolled
movement of the seat back, resulting in
possible backward collapse during
flight. Backward collapse of either crew
seat back could result in an abrupt
pitch-up if the affected crew member
continues to hold on to the control yoke
during this failure and could cause
difficulty in exiting the airplane from an
aft passenger seat after landing.
DATES: We must receive comments on
this proposed AD by October 10, 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–
0001.
• 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
this proposed AD, contact Cessna
Aircraft Company, Product Support,
P.O. Box 7706, Wichita, KS 67277;
telephone: (316) 517–5800; fax: (316)
942–9006.
FOR FURTHER INFORMATION CONTACT: Gary
Park, Aerospace Engineer, FAA, Wichita
Aircraft Certification Office, 1801
Airport Road, Mid-Continent Airport,
Wichita, Kansas 67209; telephone: (316)
946–4123; facsimile: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
(4) Do not install any rudder without the external doubler at the upper rudder hinge required by paragraph (e)(3) of this AD.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Fort Worth Aircraft
Certification Office, FAA, 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,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19.
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 the
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC, or on the Internet at http
://dms.dot.gov. The docket number is Docket
No. FAA–2006–25260; Directorate Identifier
2006–CE–37–AD.
Issued in Kansas City, Missouri, on August
3, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–12940 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–2006–25261; Directorate
Identifier 2006–CE–38–AD]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Models 172R, 172S,
182S, 182T, T182T, 206H, and T206H
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
VerDate Aug<31>2005
18:06 Aug 08, 2006
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PO 00000
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Fmt 4702
Sfmt 4702
Not Applicable.
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–2006–25261; Directorate
Identifier 2006–CE–38–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://
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
We have received reports of the crew
seat back cylinder lock bending at the
aft end and failing. We have also
received reports of cracks found in the
cylinder lock assembly.
This condition, if not corrected, could
result in failure of the crew seat back
cylinder lock assembly. This failure
could cause uncontrolled movement of
the seat back, resulting in possible
backward collapse during flight.
Backward collapse of either crew seat
back could result in an abrupt pitch-up
E:\FR\FM\09AUP1.SGM
09AUP1
]]>Agencies
[Federal Register Volume 71, Number 153 (Wednesday, August 9, 2006)]
[Proposed Rules]
[Pages 45451-45454]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-12940]
-----------------------------------------------------------------------
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
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-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,
[[Page 45452]]
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 of the airplane.
DATES: We must receive comments on this proposed AD by October 10,
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 20590-0001.
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 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-
2006-25260; Directorate Identifier 2006-CE-37-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://
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
We have 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 of the airplane.
Relevant Service Information
We have reviewed Snow Engineering Co. Service Letter 247,
dated August 14, 2005, revised May 17, 2006, 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 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.
Costs of Compliance
We estimate that this proposed AD would affect 945 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 $75,600
----------------------------------------------------------------------------------------------------------------
We have no way of determining the number of airplanes that may need
any replacements that would be required based on the results of the
proposed inspection.
We estimate the following costs to do the installation of the
external doubler at the upper rudder hinge:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
5 work-hours x $80 per hour = $400......... $217............................... $617 $583,065
----------------------------------------------------------------------------------------------------------------
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
[[Page 45453]]
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://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 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-2006-25260; Directorate Identifier
2006-CE-37-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by October 10, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
(1) AT-502 and AT-502B................. 502/502B-0003 through 502/502B-
2600.
(2) AT-502A............................ 502A-0003 through 502A-2582.
(3) AT-602............................. 602-0337 through 602-1138.
(4) AT-802 and AT-802A................. 802/802A-0001 through 802/802A-
0215.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from two reports (one Model AT-602 airplane
and one Model AT-802A airplane) of in-flight rudder separations 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 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 of the airplane.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect visually the rudder Initially inspect Follow Snow
and vertical hinge attachment upon reaching Engineering Co.
for loose fasteners; any cracks 3,500 hours time- Service Letter
in the rudder or vertical fin in-service (TIS), 247,
skins, spars, hinges or or within the dated August 14,
brackets, or corrosion. next 100 hours 2005, revised May
TIS after the 17, 2006.
effective date of
this AD,
whichever occurs
later, unless
already done.
Thereafter,
repetitively
inspect 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) dated August 14,
with new parts; and of this AD where 2005, revised May
(ii) Do the installation of the you find any 17, 2006, and
external doubler at the upper damaged parts. Snow Engineering
rudder hinge. The installation Co. Process
of the external Specification
doubler at the Number 145, dated
upper rudder December 6, 1991.
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
is the
terminating
action for the
repetitive
inspections
required by this
AD.
[[Page 45454]]
(3) Do the installation of the Upon accumulating Follow Snow
external doubler at the upper 5,000 hours TIS Engineering Co.
rudder hinge. or within the Service Letter
next 100 hours 247,
TIS after the dated August 14,
effective date of 2005, revised May
this AD, 17, 2006, and
whichever occurs Snow Engineering
later, unless Co. Process
already done. The Specification
installation of Number 145, dated
the external December 6, 1991.
doubler at the
upper rudder
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
is the
terminating
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,
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, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
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 the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC, or on the Internet at https://dms.dot.gov. The
docket number is Docket No. FAA-2006-25260; Directorate Identifier
2006-CE-37-AD.
Issued in Kansas City, Missouri, on August 3, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-12940 Filed 8-8-06; 8:45 am]
BILLING CODE 4910-13-P
