Airworthiness Directives; Air Tractor, Inc. Models AT-602, AT-802, and AT-802A Airplanes, 36863-36866 [E7-12627]

Download as PDF Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Rules and Regulations 36863 Applicability (c) This AD applies to Model DA 42 airplanes, serial numbers (S/N) 42.004 and up, certificated in any category. Diamond Aircraft Industries GmbH Aircraft Airplane Flight Manual DA 42, Doc. 7.01.05–E. approved the information collection requirements and has assigned OMB Control Number 2120–0056. FAA AD Differences Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Note: This AD differs from the MCAI and/ or service information as follows: (1) The MCAI and service bulletin require the insertion of Diamond Aircraft Airplane Flight Manual Temporary Revision ¨ Performance Data DA 42 AFM TR–MAM–42– 111/a, dated September 20, 2005, Revision 3 to the Airplane Flight Manual, or any future revision that incorporates the same information into the Diamond Aircraft Industries GmbH Aircraft Airplane Flight Manual DA 42, Doc. 7.01.05–E, immediately upon receipt. We consider immediately upon receipt as an urgent safety of flight compliance time, and we do not consider this unsafe condition to be an urgent safety of flight condition. Because we do not consider this unsafe condition to be an urgent safety of flight condition, we issued this action through the normal notice of proposed rulemaking (NPRM) AD process followed by this final rule. The time of 60 days after August 10, 2007 (the effective date of this AD) is an adequate compliance for this AD action and met the FAA requirements of an NPRM followed by a final rule. (2) Paragraphs A)i) and B)i) of the MCAI, state to assure that AFM TR–MAM–42–103, distributed with DAI MSB42–005, is inserted into AFM Doc. 7.01.05–E, rev. 2 or earlier revision. This AFM requirement was for an MCAI on which the United States did not take AD action. The action is no longer necessary when the actions in this AD are done. Therefore, the action is not being mandated in the U.S. AD action. (3) The MCAI references revision 2 of the AFM. The FAA AD references revision 3. Related Information (h) Refer to MCAI Austrian Civil Aviation Administration Austro Control GmbH AD No. A–2005–003, dated October 21, 2005; Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB–42– 006/1, dated September 20, 2005; and Diamond Aircraft Temporary Revision ¨ Performance Data DA 42 AFM TR–MAM–42– 111/a, dated September 20, 2005, for related information. jlentini on PROD1PC65 with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: It has been determined that the surface roughness of the wing stub safety walks Series 300, gray color (equals sandpaper grid 40), installed during production on some aeroplane S/Ns, adversely affects the aircraft single engine climb performance. AFM published twin engine climb performance is not affected by this AD. Actions and Compliance (f) Unless already done, do the following actions: (1) For S/N 42.004 through 42.035, and 42.037: Within 60 days after August 10, 2007 (the effective date of this AD), do the following actions following Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB–42–006/1, dated September 20, 2005: (i) Exchange the wing stub safety walks following paragraph 1.8, Action 2 a) to b) of Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB–42– 006/1, dated September 20, 2005. (ii) Insert Diamond Aircraft Airplane Flight Manual Temporary Revision Performance ¨ Data DA 42 AFM TR–MAM–42–111/a, dated September 20, 2005, Revision 3 to the Airplane Flight Manual (AFM), or any future revision that incorporates the same information into the Diamond Aircraft Industries GmbH Aircraft Airplane Flight Manual DA 42, Doc. 7.01.05–E. (2) For S/N 42.036, 42.038 through 42.064, 42.107, 42.109, 42.110, and 42.177: Within 60 days after August 10, 2007 (the effective date of this AD), insert Diamond Aircraft Airplane Flight Manual Temporary Revision ¨ Performance Data DA 42 AFM TR–MAM–42– 111/a, dated September 20, 2005, Revision 3 to the AFM, or any future revision that incorporates the same information into the Diamond Aircraft Industries GmbH Aircraft Airplane Flight Manual DA 42, Doc. 7.01.05–E. (3) For S/N 42.004 and up: Within 60 days after August 10, 2007 (the effective date of this AD), adhere to the following: (i) No wing stub safety walks Series 300 (equals sandpaper grid 40), gray color, part number (P/N) D60–1127–10–51 (no revision letter attached) may be installed as a spare part on the Model DA 42 airplane. Only Diamond Aircraft Industries (DAI) GmbH released safety walk P/Ns with a surface roughness equal to or finer than sandpaper grid 100 are approved for installation as spare parts. (ii) Diamond Aircraft Airplane Flight Manual Temporary Revision Performance ¨ Data DA 42 AFM TR–MAM–42–111/a, dated September 20, 2005, Revision 3 to the AFM, or any future revision that incorporates the same information, must remain part of VerDate Aug<31>2005 20:11 Jul 05, 2007 Jkt 211001 Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4145; fax: (816) 329–4090. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et.seq.), the Office of Management and Budget (OMB) has PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Material Incorporated by Reference (i) You must use Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB–42–006/1, dated September 20, 2005; and Diamond Aircraft Temporary Revision Performance Data DA 42 AFM TR– ¨ MAM–42–111/a, dated September 20, 2005, 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 Diamond Aircraft Industries Inc., 1560 Crumlin Sideroad, London, Ontario, Canada N5V 1S2; telephone: (519) 457–4051; fax: (800) 934–3519. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, 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/ cfr/ibr-locations.html. Issued in Kansas City, Missouri, on June 21, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–12500 Filed 7–5–07; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) that supersedes AD 2006–22–08, which E:\FR\FM\06JYR1.SGM 06JYR1 36864 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Rules and Regulations 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-inservice (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 https:// 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: Labor cost Parts cost Total cost per airplane per inspection 1.5 work-hours × $80 per hour = $120 ................................................ Not Applicable .............................. $120 jlentini on PROD1PC65 with RULES We have no way of determining the number of airplanes that may need replacement of the engine mount. We Total cost on U.S. operators for initial inspection $44,160 estimate the following costs to do the replacement: Labor cost Parts cost Total cost per airplane per replacement 81 work-hours × $80 per hour = $6,480 ......................................................................................................... $3,982 $10,462 VerDate Aug<31>2005 20:11 Jul 05, 2007 Jkt 211001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\06JYR1.SGM 06JYR1 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Rules and Regulations 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 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 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; 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 36865 [Amended] 2. The FAA amends § 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: I 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-inservice (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: Actions Compliance Procedures (1) Visually inspect the engine mount for any cracks. Initially inspect when the airplane reaches a total of 1,300 hours TIS or within the next 100 hours TIS 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. Before further flight after any inspection required by paragraph (e)(1) of this AD where crack damage is found. If you repair the cracked engine mount, then continue to reinspect at intervals not to exceed 300 hours TIS, unless the repair scheme states differently. If you replace the engine mount, then initially inspect upon accumulating 1,300 hours TIS and repetitively at intervals not to exceed 300 hours TIS. Within the next 30 days after you find the cracks or within the next 30 days after August 10, 2007 (the effective date of this AD), whichever occurs later. Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005, revised January 22, 2007. jlentini on PROD1PC65 with RULES (2) If you find any crack damage, do the following: (i) Obtain an FAA-approved repair scheme or replacement procedure from the manufacturer; and (ii) Repair following the FAA-approved repair scheme or replace the engine mount with a new engine mount following the replacement procedure. (3) Report any cracks that you find to the FAA at the address specified in paragraph (f) of this AD. Include in your report: (i) Airplane serial number; (ii) Airplane hours TIS and engine mount hours TIS; (iii) Crack location(s) and size(s); (iv) Corrective action taken; and (v) Point of contact name and telephone number. VerDate Aug<31>2005 20:11 Jul 05, 2007 Jkt 211001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 For obtaining a repair scheme or replacement procedure: Contact Air Tractor Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120–0056. E:\FR\FM\06JYR1.SGM 06JYR1 36866 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Rules and Regulations Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (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. Federal Aviation Administration Related Information 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: 14 CFR Part 39 [Docket No. FAA–2007–27432 Directorate Identifier 2007–CE–017–AD; Amendment 39–15122; AD 2007–13–18] RIN 2120–AA64 Airworthiness Directives; SOCATA— Groupe Aerospatiale Models TB9, TB10, and TB200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: (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 https://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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. The aim of the Airworthiness Directive (AD) is to introduce a new life limit for engine and Nose Landing Gear (NLG) mounts installed on EADS SOCATA TB 9, TB 10 and TB 200 airplanes, as defined in the updated Airworthiness Limitations Section (ALS) of the relevant Aircraft Maintenance Manuals (AMM). jlentini on PROD1PC65 with RULES 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] We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective 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: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That VerDate Aug<31>2005 20:11 Jul 05, 2007 Jkt 211001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 NPRM was published in the Federal Register on April 24, 2007 (72 FR 20300). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: The aim of this Airworthiness Directive (AD) is to introduce a new life limit for engine and Nose Landing Gear (NLG) mounts installed on EADS SOCATA TB 9, TB 10 and TB 200 airplanes, as defined in the updated Airworthiness Limitations Section (ALS) of the relevant Aircraft Maintenance Manuals (AMM). This AD requires introduction of the new 10,000 Flight Hour life limit for engine and NLG mounts into the operator’s maintenance program through the Revision 18 of the AMM. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 146 products of U.S. registry. We also estimate that it will take about 0.5 workhours per product to comply with basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $5,840 or $40 per product. 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 E:\FR\FM\06JYR1.SGM 06JYR1

Agencies

[Federal Register Volume 72, Number 129 (Friday, July 6, 2007)]
[Rules and Regulations]
[Pages 36863-36866]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-12627]

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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.

-----------------------------------------------------------------------

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
https://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:

----------------------------------------------------------------------------------------------------------------
Total cost on
Total cost per U.S. operators
Labor cost Parts cost airplane per for initial
inspection inspection
----------------------------------------------------------------------------------------------------------------
1.5 work-hours x $80 per hour = $120....... Not Applicable............... $120 $44,160
----------------------------------------------------------------------------------------------------------------

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:

------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane per
replacement
------------------------------------------------------------------------
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:

----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(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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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 https://
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: https://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]
BILLING CODE 4910-13-P

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