FR Doc E6-19153

[Federal Register: November 16, 2006 (Volume 71, Number 221)]
[Rules and Regulations]
[Page 66661-66663]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16no06-5]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25260; Directorate Identifier 2006-CE-37-AD;
Amendment 39-14826; AD 2006-23-14]
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), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts 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 AD requires you to
repetitively visually inspect the rudder and vertical fin hinge
attaching structure (vertical fin skins, spars, hinges, and brackets)
for loose fasteners, cracks, and/or corrosion. This AD also requires
you to replace any damaged parts found as a result of the inspection
and install an external doubler at the upper rudder hinge. This AD
results from two reports of in-flight rudder separation from the
vertical fin at the upper attach hinge area, and other reports of
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; and/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 December 21, 2006.
As of December 21, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.

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; fax: (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 20590 or on the Internet at http://dms.dot.gov.
The docket number is FAA-2006-25260; Directorate

Identifier 2006-CE-37-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; fax: (210) 308-3370.

SUPPLEMENTARY INFORMATION:

Discussion

On August 3, 2006, 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-502, AT-502A, AT-502B, AT-
602, AT-802, and AT-802A airplanes. This proposal was published in the
Federal Register as a notice of proposed rulemaking (NPRM) on August 3,
2006 (71 FR 45451). The NPRM proposed to 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.

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: Availability of Manufacturer Service Information
for the Proposed AD

Jack Buster with the Modification and Replacement Parts Association
(MARPA) provides comments on the AD process pertaining to how the FAA
addresses publishing manufacturer service information as part of a
proposed AD action. Mr. Buster states that the proposed rule attempts
to

[[Page 66662]]

require compliance with a public law by reference to a private writing
(as referenced in paragraph (e) of the proposed AD). Mr. Buster would
like the FAA to incorporate by reference (IBR) 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.
We agree with Mr. Buster. However, we do not IBR any document in a
proposed AD action, instead we IBR the document in the final rule.
Since we are issuing the proposal as a final rule AD action, the
previously-referenced Snow Engineering Co. documents are incorporated
by reference.

Comment Issue No. 2: Availability of Manufacturer Service Information
in the Federal Register or the Docket Management System (DMS)

Mr. Buster also requests IBR documents be made available to the
public by publication in the Federal Register or in the DMS.
We are currently reviewing issues surrounding the posting of
service bulletins in the Department of Transportation's DMS as part of
the AD docket. Once we have thoroughly examined all aspects of this
issue and have made a final determination, we will consider whether our
current practice needs to be revised.

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 945 airplanes in the U.S.
registry.
We estimate the following costs to do the 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
----------------------------------------------------------------------------------------------------------------

Any required ``upon-condition'' repairs will vary depending upon
the damage found, and any replacements required will vary based on the
results of the inspection. Based on this, we have no way of determining
the potential repair and/or replacement costs for each airplane or the
number of airplanes that will need the repairs and/or replacements
based on the result of the inspections.
We estimate the following costs to do the 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 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-2006-25260; Directorate Identifier 2006-CE-37-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. FAA amends Sec. 39.13 by adding a new AD to read as follows:

2006-23-14 Air Tractor, Inc.: Amendment 39-14826; Docket No. FAA-
2006-25260; Directorate Identifier 2006-CE-37-AD.

Effective Date

(a) This AD becomes effective on December 21, 2006.

[[Page 66663]]

Affected ADs

(b) None.

Applicability

------------------------------------------------------------------------
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.
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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; and/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:

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Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect visually the Initially inspect Follow Snow
rudder and vertical hinge upon reaching 3,500 Engineering Co.
attachment for loose hours time-in- Service Letter
fasteners; and inspect the service (TIS), or 247, dated
rudder or vertical fin within the next 100 August 14, 2005,
skins, spars, hinges or hours TIS after revised May 17,
brackets for cracks and/or December 21, 2006 2006.
corrosion. (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.
(2) If you find any damage Before further Follow Snow
as a result of any flight after any Engineering Co.
inspection required by inspection required Service Letter
paragraph (e)(1) of this by paragraph (e)(1) 247, dated
AD, you must: of this AD where August 14, 2005,
(i) Replace any damaged you find any revised May 17,
parts with new parts; and damaged parts. The 2006, and Snow
(ii) Do the installation of installation of the Engineering Co.
the external doubler at the external doubler at Process
upper rudder hinge. the upper rudder Specification
hinge required by Number 145, dated
paragraph December 6, 1991.
(e)(2)(ii) or
(e)(3) of this AD
is the terminating
action for the
repetitive
inspections
required by this AD.
(3) Do the installation of Upon accumulating Follow Snow
the external doubler at the 5,000 hours TIS or Engineering Co.
upper rudder hinge. within the next 100 Service Letter
hours TIS after the 247, dated
effective date of August 14, 2005,
this AD, whichever revised May 17,
occurs later, 2006, and Snow
unless already Engineering Co.
done. The Process
installation of the Specification
external doubler at Number 145, dated
the 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.
(4) Do not install any As of December 21, Not Applicable.
rudder without the external 2006 (the effective
doubler at the upper rudder date of this AD).
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; fax: (210) 308-3370, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.

Material Incorporated by Reference

(g) You must use 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, 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; fax: (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 November 3, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19153 Filed 11-15-06; 8:45 am]

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