Airworthiness Directives; Air Tractor, Inc. Models AT-402, AT-402A, and AT-402B Airplanes

[Federal Register Volume 73, Number 201 (Thursday, October 16, 2008)]
[Rules and Regulations]
[Pages 61343-61346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-24137]


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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.

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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 
<greek-i>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: 
[email protected]; Web site: http://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 
http://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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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      <greek-i>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         <greek-i>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           <greek-i>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 
<greek-i>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 
<greek-i>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: [email protected]; 
Web site: http://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: http://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

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