Airworthiness Directives; Air Tractor, Inc. Models AT-402, AT-402A, and AT-402B Airplanes, 61343-61346 [E8-24137]

Download as PDF 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 VerDate Aug<31>2005 16:18 Oct 15, 2008 Jkt 217001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 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 E:\FR\FM\16OCR1.SGM 16OCR1 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 VerDate Aug<31>2005 16:18 Oct 15, 2008 Jkt 217001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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: ■ E:\FR\FM\16OCR1.SGM 16OCR1 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 Frm 00021 Fmt 4700 Sfmt 4700 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. E:\FR\FM\16OCR1.SGM 16OCR1 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. VerDate Aug<31>2005 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 PO 00000 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 16OCR1

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
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