[Federal Register: July 6, 2007 (Volume 72, Number 129)]
[Rules and Regulations]
[Page 36863-36866]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06jy07-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27212; Directorate Identifier 2007-CE-011-AD;
Amendment 39-15121; AD 2007-13-17]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-602, AT-
802, and AT-802A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 2006-22-08, which
[[Page 36864]]
applies to all Air Tractor, Inc. (Air Tractor) Models AT-602, AT-802,
and AT-802A airplanes. AD 2006-22-08 currently requires you to
repetitively inspect the engine mount for any cracks, repair or replace
any cracked engine mount, and report any cracks found to the FAA. Since
we issued AD 2006-22-08, the FAA has received reports of two Model AT-
802A airplanes with cracked engine mounts below the initial compliance
time in AD 2006-22-08. The FAA has determined that an initial
inspection is required when the airplane reaches a total of 1,300 hours
time-in-service (TIS) instead of 4,000 hours TIS required by AD 2006-
22-08. Consequently, this AD retains the actions of AD 2006-22-08 while
requiring the initial inspection when the airplane reaches a total of
1,300 hours TIS. We are issuing this AD to detect and correct cracks in
the engine mount, which could result in failure of the engine mount.
Such failure could lead to separation of the engine from the airplane.
DATES: This AD becomes effective on August 10, 2007.
On August 10, 2007, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: To get the 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.
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
http://dms.dot.gov. The docket number is FAA-2007-27212; Directorate
Identifier 2007-CE-011-AD.
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:
Discussion
On March 8, 2007, 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 all Air Tractor Models AT-602, AT-802, and AT-802A
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on March 15, 2007 (72 FR 12131).
The NPRM proposed to retain the actions of AD 2006-22-08 while
requiring the initial inspection at 1,300 hours TIS.
Comments
We provided the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and FAA's response to each comment:
Comment Issue No. 1: Installation of a Welded Gusset Is Terminating
Action for the Proposed Inspections
Leland Snow, President of Air Tractor, Inc., believes that Snow
Engineering Co. Report Number 1727, Revision A, dated April 12, 2007
(referred to after this as Report 1727), justifies terminating action
for the proposed inspections. Mr. Snow states that installation of a
welded gusset following Snow Engineering Co. Service Letter
253, dated December 12, 2005, revised January 22, 2007, would
eliminate the need for such inspections.
Based on the information presented in Report 1727, the FAA finds
that the installation of the welded gusset does not fully address the
unsafe condition and cannot be considered as a terminating action for
the repetitive inspection.
We are making no changes to the final rule AD action based on this
comment.
Comment Issue No. 2: FAA Has Overstated the Consequences of Cracks in
the Engine Mount
Mr. Snow also states that the FAA overstates the events that would
occur should cracks found in service result in the engine mount tube
separating from the engine mount ring. He also states that the engine
mount ring would remain attached to the remaining tube connections and
prevent the engine from separating from the airplane.
The commenter did not provide any analysis or data to show that
this situation would not occur. Based on the FAA's evaluation of the
unsafe condition, we believe there is potential for the engine mount
tube to separate from the engine mount ring.
Without the data to show that the engine mount ring would remain
attached to the remaining tube connections, the FAA cannot change the
potential end result condition of the engine separating from the
airplane.
We are not changing the final rule AD action as a result of these
comments.
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 368 airplanes in the U.S.
registry.
We estimate the following costs to do each required inspection:
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Total cost on
Total cost per U.S. operators
Labor cost Parts cost airplane per for initial
inspection inspection
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1.5 work-hours x $80 per hour = $120....... Not Applicable............... $120 $44,160
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We have no way of determining the number of airplanes that may need
replacement of the engine mount. We estimate the following costs to do
the replacement:
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Total cost per
Labor cost Parts cost airplane per
replacement
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81 work-hours x $80 per hour = $3,982 $10,462
$6,480...........................
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[[Page 36865]]
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-2007-27212; Directorate Identifier 2007-CE-011-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:
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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2006-22-08, Amendment 39-14805 (71 FR 62910, October 27, 2006), and
adding the following new AD:
2007-13-17 Air Tractor, Inc.: Amendment 39-15121; Docket No. FAA-
2007-27212; Directorate Identifier 2007-CE-011-AD.
Effective Date
(a) This AD becomes effective on August 10, 2007.
Affected ADs
(b) This AD supersedes AD 2006-22-08, Amendment 39-14805.
Applicability
(c) This AD affects all Models AT-602, AT-802, and AT-802A
airplanes, all serial numbers, that are certificated in any
category.
Unsafe Condition
(d) This AD results from reports of two Model AT-802A airplanes
with cracked engine mounts (at 2,815 hours time-in-service (TIS) and
1,900 hours TIS) below the initial compliance time in AD 2006-22-08.
The FAA has determined that an initial inspection when the airplane
reaches a total of 1,300 hours TIS is required instead of 4,000
hours TIS as required by AD 2006-22-08. We are issuing this AD to
detect and correct cracks in the engine mount, which could result in
failure of the engine mount. Such failure could lead to separation
of the engine from the airplane.
Compliance
(e) To address this problem, you must do the following, unless
already done:
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Actions Compliance Procedures
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(1) Visually inspect the engine Initially inspect when the airplane Follow Snow Engineering Co. Service
mount for any cracks. reaches a total of 1,300 hours TIS Letter 253, dated December
or within the next 100 hours TIS 12, 2005, revised January 22, 2007.
after August 10, 2007 (the
effective date of this AD),
whichever occurs later, unless
already done. Thereafter, inspect
repetitively at intervals not to
exceed 300 hours TIS.
(2) If you find any crack damage, do Before further flight after any For obtaining a repair scheme or
the following: inspection required by paragraph replacement procedure: Contact Air
(i) Obtain an FAA-approved repair (e)(1) of this AD where crack Tractor Inc., P.O. Box 485, Olney,
scheme or replacement procedure damage is found. If you repair the Texas 76374; telephone: (940) 564-
from the manufacturer; and cracked engine mount, then continue 5616; facsimile: (940) 564-5612.
(ii) Repair following the FAA- to reinspect at intervals not to
approved repair scheme or replace exceed 300 hours TIS, unless the
the engine mount with a new engine repair scheme states differently.
mount following the replacement If you replace the engine mount,
procedure. then initially inspect upon
accumulating 1,300 hours TIS and
repetitively at intervals not to
exceed 300 hours TIS.
(3) Report any cracks that you find Within the next 30 days after you The Office of Management and Budget
to the FAA at the address specified find the cracks or within the next (OMB) approved the information
in paragraph (f) of this AD. 30 days after August 10, 2007 (the collection requirements contained
Include in your report: effective date of this AD), in this regulation under the
(i) Airplane serial number; whichever occurs later. provisions of the Paperwork
(ii) Airplane hours TIS and engine Reduction Act of 1980 (44 U.S.C.
mount hours TIS; 3501 et seq.) and assigned OMB
(iii) Crack location(s) and size(s); Control Number 2120-0056.
(iv) Corrective action taken; and
(v) Point of contact name and
telephone number.
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[[Page 36866]]
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.
(g) AMOCs approved for AD 2006-22-08 are not approved for this
AD.
Related Information
(h) 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 http://dms.dot.gov.
The docket number is Docket No. FAA-2007-27212;
Directorate Identifier 2007-CE-011-AD.
Material Incorporated by Reference
(i) You must use Snow Engineering Co. Service Letter
253, dated December 12, 2005, revised January 22, 2007, 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 Air
Tractor Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; facsimile: (940) 564-5612.
(3) 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Kansas City, Missouri, on June 22, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-12627 Filed 7-5-07; 8:45 am]
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