Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes, 52255-52263 [2010-20555]

Download as PDF Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 23, Issue 3, dated August 5, 2010, for related information. Material Incorporated by Reference (i) You must use GippsAero Pty. Ltd. Mandatory Service Bulletin SB–GA8–2005– 23, Issue 3, dated August 5, 2010, 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 GippsAero Pty. Ltd., Attn: Technical Services, P.O. Box 881, Morwell, Victoria 3840, Australia; telephone: + 61 03 5172 1200; fax: +61 03 5172 1201; Internet: https://www.gippsaero.com. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD 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 August 18, 2010. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–21063 Filed 8–24–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0827; Directorate Identifier 2010–CE–029–AD; Amendment 39–16412; AD 2010–17–18] RIN 2120–AA64 Airworthiness Directives; Air Tractor, Inc. Models AT–802 and AT–802A Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. mstockstill on DSKH9S0YB1PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) to supersede AD 2010–13–08, which applies to all Air Tractor, Inc. (Air Tractor) Models AT–802 and AT–802A airplanes. AD 2010–13–08 currently requires you to repetitively inspect (using the eddy current method) the two SUMMARY: VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar cap. Since we issued 2010–13–08, we evaluated service information issued by Air Tractor and determined we need to add inspections, add modifications, and change the safe life for certain serial number (SN) ranges. Consequently, this AD would retain the actions of AD 2010–13–08 and would add inspections, add modifications, and change the safe life for certain SN ranges. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane. This AD becomes effective on September 9, 2010. On September 9, 2010, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #281, dated August 1, 2009; Snow Engineering Co. Service Letter #245, dated April 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009, listed in this AD. As of April 21, 2006 (71 FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter #240, dated September 30, 2004; and Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002, listed in this AD. We must receive any comments on this AD by October 12, 2010. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., DATES: PO 00000 Frm 00043 Fmt 4700 Sfmt 4700 52255 Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; fax: (940) 564–5612; E-mail: airmail@airtractor.com; Internet: https:// www.airtractor.com. To view the comments to this AD, go to https://www.regulations.gov. The docket number is FAA–2010–0827; Directorate Identifier 2010–CE–029–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 Since 2000, we have issued several ADs related to the wing spar inspection and safe life on Air Tractor AT–400, AT–500, AT–600, and AT–800 series airplanes. In 2001, we issued AD 2001–10–04, Amendment 39–12230 (66 FR 27014, May 16, 2001) to lower the safe life for the wing lower spar cap on Air Tractor AT–400, AT–500, and AT–800 series airplanes. This AD allowed for inspection (using eddy current methods) of the wing lower spar cap for airplanes that were at or over the lower safe life and for which parts were not available. Later that same year, we revised that AD to remove AT–800 series airplanes from the applicability that were equipped with the factory-supplied computerized fire gate (part number 80540) and engaged in full-time firefighting. In 2002, we issued AD 2002–11–05, Amendment 39–12766 (67 FR 37967, May 31, 2002) that retained the actions for the AT–802 series airplanes and further reduced the safe life for certain AT–400 series airplanes and certain AT–500 series airplanes that either incorporate or have incorporated Marburger winglets. After receiving reports of fatigue cracking found on three Model AT– 802A airplanes that were below the reduced safe life established in AD 2001–10–04, we issued AD 2006–08–09, Amendment 39–14565 (71 FR 27794, May 12, 2006). AD 2006–08–09 required repetitively inspecting the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repairing or replacing any cracked spar cap. After issuing AD 2006–08–09, we determined the need to clarify the affected SN applicability. Models AT– E:\FR\FM\25AUR1.SGM 25AUR1 52256 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 802 and AT–802A share a common SN range. Sometimes service information listed only one of the models with a starting or ending SN within a SN range, depending on which model was produced with that specific SN, even though the service information applied to both models. We superseded AD 2006–08–09 and issued AD 2010–13–08, Amendment 39–16339 (75 FR 35616, June 23, 2010) to retain the actions from AD 2006–08–09, clarify serial number applicability, and add an option of modifying the wing main spar lower caps to extend the safe life limit. After completing fatigue analysis on Models AT–802 and AT–802A airplanes, Air Tractor issued service information that adds inspections, adds modifications, and changes the safe life for certain SN ranges. Since we issued 2010–13–08, we evaluated this new service information and determined the need to add inspections, add modifications, and change the safe life for certain SN ranges. This condition, if not corrected, could result in failure of the spar cap and lead to wing separation and loss of control of the airplane. mstockstill on DSKH9S0YB1PROD with RULES Relevant Service Information We reviewed the following service information from Snow Engineering Co.: • Service Letter #80GG, revised December 21, 2005; • Service Letter #284, dated October 4, 2009; • Service Letter #281, dated August 1, 2009; • Service Letter #245, dated April 25, 2005; • Service Letter #240, dated September 30, 2004; • Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 • Drawing Number 20995, Sheet 3, dated November 25, 2005; • Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and • Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009. The service information describes procedures for the following actions: • Inspection (repetitively) of the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks; • Repair or replacement of any cracked spar cap; and • Modification option to extend the safe life limit. FAA’s Determination and Requirements of This AD We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires you to repetitively inspect (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar cap. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, 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 an opportunity for public comment. We PO 00000 Frm 00044 Fmt 4700 Sfmt 4700 invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ‘‘FAA–2010– 0827; Directorate Identifier 2010–CE– 029–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD. 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 rulemaking action. E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations Regulatory Flexibility Determination The Regulatory Flexibility Act of 1980 (Pub. L. 96–354) (RFA) establishes as a principle of regulatory issuance that agencies shall endeavor, consistent with the objective of the rule and of applicable statutes, to fit regulatory and informational requirements to the scale of the businesses, organizations, and governmental jurisdictions subject to regulation. To achieve that principle, the RFA requires agencies to solicit and consider flexible regulatory proposals and to explain the rationale for their actions. The RFA covers a wide-range of small entities, including small businesses, not-for-profit organizations, and small governmental jurisdictions. Agencies must perform a review to determine whether a proposed or final rule will have a significant economic impact on a substantial number of small entities. In accordance with Section 608 of the Regulatory Flexibility Act, an agency head may waive or delay completion of some or all of the requirements of Section 603 by providing a written finding that this final rule is being promulgated in response to an emergency that makes compliance or timely compliance with the provisions of Section 603 impracticable. We are performing a review to determine whether this final rule AD action will have a significant economic impact on a substantial number of small entities. However, the immediate safety of flight conditions of this AD action make compliance with the provisions of Section 603 impracticable. Our justification for immediate adoption of this rule, and therefore of impracticability, is stated in FAA’s Justification and Determination of the Effective Date. After we determine 52257 whether this final rule AD action has a significant economic impact on a substantial number of small entities or not, we will publish in the Federal Register our determination and, if required, our final regulatory flexibility analysis. 2010–17–18 Air Tractor, Inc.: Amendment 39–16412; Docket No. FAA–2010–0827; Directorate Identifier 2010–CE–029–AD. Examining the AD Docket Affected ADs You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647– 5527) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (a) This AD becomes effective on September 9, 2010. (b) This AD supersedes AD 2010–13–08; Amendment 39–16339. Applicability (c) This AD affects Models AT–802 and AT–802A airplanes, all serial numbers (SNs) beginning with –0001, that are: (1) Certificated in any category; (2) Engaged in agricultural dispersal operations, including those airplanes that have been converted from fire fighting to agricultural dispersal or airplanes that convert between fire fighting and agricultural dispersal; (3) Not equipped with the factory-supplied computerized fire gate (part number (P/N) 80540); and (4) Not engaged in only full-time fire fighting. Subject Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 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 Effective Date [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2010–13–08, Amendment 39–16339 (75 FR 35616, June 23, 2010), and by adding a new AD to read as follows: ■ (d) Air Transport Association of America (ATA) Code 57: Wings. Unsafe Condition (e) This AD results from our determination that we need to require the actions in the new service information to add inspections, add modifications, and change the safe life for certain SN ranges. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane. Compliance (f) To address this problem for Models AT–802 and AT–802A airplanes, SNs –0001 through –0091, you must do the following, unless already done: TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES Compliance Procedures (1) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. mstockstill on DSKH9S0YB1PROD with RULES Actions Initially inspect upon accumulating 1,700 hours time-in-service (TIS) or within the next 50 hours TIS after April 21, 2006 (the effective date of AD 2006–08–09), whichever occurs later, and repetitively thereafter at intervals not to exceed 800 hours TIS. If, before September 9, 2010 (the effective date of this AD), you installed the center splice plate and extended 8-bolt splice blocks, use the inspection compliance times found in paragraph (f)(5) of this AD. Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002. VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 PO 00000 Frm 00045 Fmt 4700 Sfmt 4700 E:\FR\FM\25AUR1.SGM 25AUR1 52258 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued Compliance Procedures (2) If you find any cracks as a result of any inspection required in paragraph (f)(1) of this AD, do the following actions: (i) For cracks that can be repaired, repair the airplane by doing the following actions: (A) Install center splice plate, P/N 20997– 2, and extended 8-bolt splice blocks, P/N 20985–1 & –2, and cold-work the lower spar cap fastener holes; and (B) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the modification and is separate from the inspections required in paragraph (f)(1) of this AD. (ii) For cracks that cannot be repaired by incorporating the modification specified above, do the actions to replace the lower spar caps and associated parts listed following the procedures identified in paragraph (f)(3) of this AD. (3) Replace the wing main spar lower caps, the web plates, the center joint splice blocks and hardware, and the wing attach angles and hardware, and install the steel web splice plate. This replacement terminates the repetitive inspections required in paragraph (f)(1) of this AD. mstockstill on DSKH9S0YB1PROD with RULES Actions Before further flight after the inspection where a crack was found. If, before the airplane reaches a total of 3,200 hours TIS, you repair your airplane following paragraph (f)(2)(i) of this AD, you must do the eddy current inspections following the compliance times found in paragraph (f)(5) of this AD. If, at 3,200 hours TIS or after, you repair your airplane following paragraph (f)(2)(i) of this AD, this repair terminates the inspection requirements of paragraph (f)(1) of this AD. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Service Letter #240, dated September 30, 2004. (i) Do the replacement at whichever of the following compliance times occurs first: (A) Before further flight when cracks are found that cannot be repaired by incorporating the modification in paragraph (f)(2)(i) of this AD; or (B) Before or when the airplane reaches the wing main spar lower cap safe life of a total of 4,100 hours TIS or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. (ii) After this replacement the new spar safe life is 11,700 hours TIS. If, before September 9, 2010 (the effective date of this AD), an airplane main spar lower cap was replaced with P/N 21083–1/–2, the spar safe life for that P/N spar cap is 8,000 hours TIS until the main spar lower cap is replaced with P/N 21118–1/–2. The new spar safe life for P/N 21118–1/–2 is 11,700 hours. (iii) To extend the initial 4,100 hours TIS safe life of the wing main spar lower cap to a total of 8,000 hours TIS, you may incorporate the optional modification specified in paragraph (f)(4) of this AD. Modify at whichever of the following compliance times occurs first: (A) Before further flight after any inspection required in paragraph (f)(1) of this AD where a crack is found. If you modify your airplane before the airplane reaches a total of 3,200 hours TIS to repair cracks as required in paragraph (f)(2)(i) of this AD, you must do the eddy current inspections following the compliance times found in paragraph (f)(5) of this AD. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A, dated January 7, 2009. (4) To extend the safe life of the wing main spar lower cap to a total of 8,000 hours TIS, you may incorporate the following optional modification. This modification terminates the repetitive inspections required in paragraph (f)(1) of this AD, unless you performed the modification before the airplane reaches a total of 3,200 hours TIS to repair cracks: (i) Install center splice plate, P/N 20997–2, and extended 8-bolt splice blocks, P/N 20985–1 & –2, and cold-work the lower spar cap fastener holes; and VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 PO 00000 Frm 00046 Fmt 4700 Sfmt 4700 Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Service Letter #240, dated September 30, 2004. E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52259 TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued Actions Compliance (ii) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the modification and is separate from the inspections required in paragraph (f)(1) of this AD. (B) Between 3,200 hours TIS and 4,100 hours TIS. (5) If, before September 9, 2010 (the effective date of this AD) or as a result of performing the repair for cracks following paragraph (f)(2) of this AD, you installed the center splice plate and extended 8-bolt splice Procedures blocks, use the following table for compliance times to do the eddy current inspections required in paragraph (f)(1) of this AD. If you find any cracks as a result of any inspection following the compliance times in the following table, you must do the replacement action in paragraph (f)(2)(ii) of this AD: TABLE 2—EDDY CURRENT INSPECTION COMPLIANCE TIMES Condition of the airplane Initially inspect Repetitively inspect thereafter at intervals not to exceed (i) If the airplane has already had the center splice plate and extended 8-bolt splice blocks installed at or after 3,200 hours TIS but the fastener holes have not been cold worked, at any time you may cold work the fastener holes to terminate the repetitive inspection requirements of this paragraph. (ii) Before reaching 3,200 hours TIS, the airplane had the center splice plate and extended 8-bolt splice blocks already installed but the fastener holes have not been cold worked. (iii) Before reaching 3,200 hours TIS, the airplane had the center splice plate and extended 8-bolt splice blocks installed and the fastener holes have been cold worked. When the airplane reaches a total of 2,400 hours TIS after the modification or within the next 100 days after September 9, 2010 (the effective date of this AD), whichever occurs later. 1,200 hours TIS until the 8,000 hours TIS spar replacement time. When the airplane reaches a total of 2,400 hours TIS after the modification or within the next 100 days after September 9, 2010 (the effective date of this AD), whichever occurs later. When the airplane reaches a total of 4,800 hours TIS after the modification or within the next 100 days after September 9, 2010 (the effective date of this AD), whichever occurs later. 1,200 hours TIS. Upon reaching 4,800 hours TIS after the modification, inspect repetitively thereafter at intervals not to exceed 600 hours TIS until the 8,000 hours TIS spar replacement time. 600 hours TIS until the 8,000 hours TIS spar replacement time. (g) To address this problem for AT–802 and AT–802A airplanes, SNs –0092 through –0101, you must do the following, unless already done: TABLE 3—ACTIONS, COMPLIANCE, AND PROCEDURES Compliance Procedures (1) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. mstockstill on DSKH9S0YB1PROD with RULES Actions Initially inspect upon accumulating 1,700 hours TIS or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later, and repetitively thereafter at intervals not to exceed 800 hours TIS. If the center splice plate, P/N 20994–2, is installed as specified in paragraph (g)(4) of this AD, do the repetitive inspections at intervals not to exceed 2,000 hours TIS. Before further flight after the inspection where a crack was found. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; and Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002. (2) If you find any cracks as a result of any inspection required by paragraph (g)(1) of this AD, do the following actions. This repair modification terminates the repetitive inspections required in paragraph (g)(1) of this AD: (i) For cracks that can be repaired, repair the airplane by doing the following actions: (A) Install the 9-bolt splice blocks and coldwork the lower spar cap fastener holes; VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 PO 00000 Frm 00047 Fmt 4700 Sfmt 4700 Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; and Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002, Snow Engineering Co. Service Letter #281, dated August 1, 2009; and Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005. E:\FR\FM\25AUR1.SGM 25AUR1 52260 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations TABLE 3—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued Actions Compliance mstockstill on DSKH9S0YB1PROD with RULES (B) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the repair and is separate from the inspections required in paragraph (g)(1) of this AD; and (C) Install the center splice plate, P/N 20994–2, per paragraph (g)(4) if not already installed. (ii) For cracks that cannot be repaired by doing the actions in paragraph (g)(2)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures identified in paragraph (g)(3) of this AD. (3) Replace the wing main spar lower caps, the web plates, the center joint splice blocks and hardware, and the wing attach angles and hardware, and install the steel web splice plate. This replacement terminates the repetitive inspections required in paragraph (g)(1) of this AD. (4) To extend the safe life of the wing main spar lower cap to a total of 8,000 hours TIS, you may incorporate the following optional modification: (i) Install center splice plate, P/N 20994–2, if not already installed as part of a repair, and cold-work the lower spar cap fastener holes; and (ii) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the modification and is separate from the inspections required in paragraph (g)(1) of this AD. (5) If you find any cracks as a result of any repetitive inspection required by paragraph (g)(4) of this AD, do the following actions. This repair modification terminates the repetitive inspections required in paragraph (g)(4) of this AD: (i) For cracks that can be repaired, repair the airplane by doing the following actions: (A) Install the 9-bolt splice blocks and coldwork the lower spar cap fastener holes; and VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 Procedures (i) Do the replacement at whichever of the following compliance times occurs first: (A) Before further flight when cracks are found that cannot be repaired by incorporating the modification in paragraph (g)(2)(i) of this AD; or (B) Before or when the airplane reaches the wing main spar lower cap safe life of a total of 4,100 hours TIS or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. (ii) To extend the initial 4,100 hours TIS safe life of the wing main spar lower cap to a total of 8,000 hours TIS, you may incorporate the optional modification specified in paragraph (g)(4) of this AD. (iii)After replacement of the old spar with the new lower spar cap, P/N 21118–1/ –2, the new spar safe life is 11,700 hours TIS. Before the airplane reaches a total of 4,100 hours TIS. After installation of the center splice plate, P/N 20994–2, do the repetitive inspections required in paragraph (g)(1) at intervals not to exceed 2,000 hours TIS. If as of September 9, 2010 (the effective date of this AD) you have already exceeded the 4,100 hours TIS threshold for extending the safe life to 8,000 hours TIS, you may be eligible for an alternative method of compliance following paragraph (m) in this AD. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A, dated January 7, 2009. Before further flight after the inspection where a crack was found. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; and Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002, Snow Engineering Co. Service Letter #281, dated August 1, 2009; and Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005. PO 00000 Frm 00048 Fmt 4700 Sfmt 4700 Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009; and Snow Engineering Co. Service Letter #245, dated April 25, 2005. E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52261 TABLE 3—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued Actions Compliance Procedures (B) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the repair and is separate from the inspections required in paragraph (g)(1) of this AD. (ii) For cracks that cannot be repaired by doing the actions in paragraph (g)(5)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures identified in paragraph (g)(3) of this AD. (h) To address this problem for AT–802 and AT–802A airplanes, SNs –0102 through –0178, you must do the following, unless already done: TABLE 4—ACTIONS, COMPLIANCE, AND PROCEDURES Compliance Procedures (1) Do an initial eddy current inspection for cracks of the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. After this initial inspection, you may do the optional cold-working of the lower spar cap fastener holes to increase the hours TIS between repetitive inspections required in paragraph (h)(2) of this AD. (2) Repetitively eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. mstockstill on DSKH9S0YB1PROD with RULES Actions Before the airplane reaches a total of 5,500 hours TIS or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Service Letter #245, dated April 25, 2005; and Snow Engineering Co. Service Letter #284, dated October 4, 2009. Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Service Letter #284, dated October 4, 2009; and (optional) Snow Engineering Co. Service Letter #245, dated April 25, 2005. Follow Snow Engineering Co. Service Letter #281, dated August 1, 2009; and Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005. (3) If you find any cracks as a result of any inspection required by paragraphs (h)(1) and (h)(2) of this AD, do the following actions. This modification terminates the repetitive inspections required in paragraph (h)(1) and (h)(2) of this AD: (i) For cracks that can be repaired, repair the airplane by doing the following actions: (A) Install the 9-bolt splice blocks and coldwork the lower spar cap fastener holes; and (B) Eddy current inspect for cracks the center splice joint outboard two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the repair and is separate from the inspections required in paragraphs (h)(1) and (h)(2) of this AD. (ii) For cracks that cannot be repaired by doing the actions in paragraph (h)(3)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures in paragraph (h)(4) of this AD. VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 (i) For fastener holes that are cold-worked: After the initial inspection, repetitively thereafter inspect at intervals not to exceed 2,200 hours TIS. (ii) For fastener holes not cold-worked: After the initial inspection, repetitively thereafter inspect at intervals not to exceed 1,100 hours TIS. Before further flight after the inspection where a crack was found. PO 00000 Frm 00049 Fmt 4700 Sfmt 4700 E:\FR\FM\25AUR1.SGM 25AUR1 52262 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations TABLE 4—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued Actions Compliance Procedures (4) Replace the wing main spar lower caps, the web plates, the center joint splice blocks and hardware, and the wing attach angles and hardware, and install the steel web splice plate. This replacement terminates the repetitive inspections required in paragraphs (h)(1) and (h)(2) of this AD. (i) Do the replacement at whichever of the following compliance times occurs first: (A) Before further flight when cracks are found that cannot be repaired by incorporating the repair in paragraph (h)(3)(i) of this AD; or (B) Before or when the airplane reaches the wing main spar lower cap safe life of a total of 8,000 hours TIS or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. (ii) After this replacement the new spar safe life is 11,700 hours TIS. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A, dated January 7, 2009. (i) To address this problem for AT–802 and AT–802A airplanes, SNs –0179 through –0269, you must do the following, unless already done: TABLE 5—ACTIONS, COMPLIANCE, AND PROCEDURES Actions Compliance Procedures Replace the wing main spar lower caps, the web plates, the center joint splice blocks and hardware, and the wing attach angles and hardware, and install the steel web splice plate. By the 8,000 hours TIS safe-life or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. After this replacement the subsequent new spar safe life is 11,700 hours TIS. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A, dated January 7, 2009. (j) To address this problem for AT–802 and AT–802A airplanes, SNs –0270 and subsequent, you must do the following, unless already done: TABLE 6—ACTIONS, COMPLIANCE, AND PROCEDURES Actions Compliance Procedures Replace the wing main spar lower caps, the web plates, the center joint splice blocks and hardware, and the wing attach angles and hardware, and install the steel web splice plate. By the 11,700 hours TIS safe-life or within the next 50 hours TIS after September 9, 2010 (the effective date of this AD), whichever occurs later. After this replacement the subsequent new spar safe life is 11,700 hours TIS. Follow Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A, dated January 7, 2009. (k) Report any crack from any inspection required in paragraphs (f), (g), or (h) of this AD within 10 days after the cracks are found on the form in Figure 1 of this AD. (1) Send your report to 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. (2) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act and assigned OMB Control Number 2120–0056. Special Permit Flight (l) Under 14 CFR part 39.23, we are allowing special flight permits for the purpose of compliance with this AD under the following conditions: (1) Only operate in day visual flight rules (VFR). (2) Ensure that the hopper is empty. (3) Limit airspeed to 135 miles per hour (mph) indicated airspeed (IAS). (4) Avoid any unnecessary g-forces. (5) Avoid areas of turbulence. (6) Plan the flight to follow the most direct route. AD 2010–17–18 INSPECTION REPORT mstockstill on DSKH9S0YB1PROD with RULES [REPORT ONLY IF CRACKS ARE FOUND] General Information 1. Inspection Performed By: 2. Phone: 3. Aircraft Model: 4. Aircraft Serial Number: 5. Engine Model Number: 6. Aircraft Total Hours TIS: VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 PO 00000 Frm 00050 Fmt 4700 Sfmt 4700 E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52263 AD 2010–17–18 INSPECTION REPORT—Continued [REPORT ONLY IF CRACKS ARE FOUND] 7. Wing Total Hours TIS: 8. Lower Spar Cap Hours TIS: Previous Inspection/Repair History 9. Has the lower spar cap been inspected (eddy-current, dye penetrant, magnetic particle, or ultrasound) before? b Yes b No If yes, an inspection has occurred: Date:llllllllllll Inspection Method:llllll Lower Spar Cap TIS:llllll Cracks found? b Yes b No 10. Has there been any major repair or alteration performed to the spar cap? b Yes b No If yes, specify (Description and hours TIS): Inspection for AD 2010–17–18 11. Date of AD inspection: Inspection Results: 11a. Cracks found: b Left Hand b Right Hand 11b. Crack Length:______ 11c. Does drilling hole to next larger size remove all traces of the crack(s)? b Yes b No Location:______ 12d. Corrective Action Taken: Mail report (only if you find any cracks as a result of the inspection for AD 2010–17–18) to: 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. Figure 1 mstockstill on DSKH9S0YB1PROD with RULES Alternative Methods of Compliance (AMOCs) (m) 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: Andy McAnaul, Aerospace Engineer, ASW–150, FAA San Antonio MIDO–43, 10100 Reunion Pl., Ste. 650, San Antonio, Texas 78216, phone: (210) 308–3365, fax: (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. (n) AMOCs approved for AD 2010–13–08 are not approved for this AD. Material Incorporated by Reference (o) You must use Snow Engineering Co. Service Letter #80GG, revised December 21, 2005; Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #281, dated August 1, 2009; Snow Engineering Co. Service Letter #245, dated April 25, 2005; Snow Engineering Co. Service Letter #240, dated September 30, 2004; Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009, 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 #80GG, VerDate Mar<15>2010 17:51 Aug 24, 2010 Jkt 220001 revised December 21, 2005; Snow Engineering Co. Service Letter #284, dated October 4, 2009; Snow Engineering Co. Service Letter #281, dated August 1, 2009; Snow Engineering Co. Service Letter #245, dated April 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) On April 21, 2006 (71 FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter #240, dated September 30, 2004; and Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002. (3) For service information identified in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; fax: (940) 564–5612; E-mail: airmail@airtractor.com; Internet: https:// www.airtractor.com. (4) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (5) You may also review copies of the service information incorporated by reference for this AD 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. PO 00000 Frm 00051 Fmt 4700 Sfmt 4700 Issued in Kansas City, Missouri on August 11, 2010. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–20555 Filed 8–24–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0497; Directorate Identifier 2009–NM–019–AD; Amendment 39–16417; AD 2010–18–04] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes; and Model ERJ 190–100 LR, –100 IGW, –100 STD, –200 STD, –200 LR, and –200 IGW Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation SUMMARY: E:\FR\FM\25AUR1.SGM 25AUR1

Agencies

[Federal Register Volume 75, Number 164 (Wednesday, August 25, 2010)]
[Rules and Regulations]
[Pages 52255-52263]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-20555]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0827; Directorate Identifier 2010-CE-029-AD;
Amendment 39-16412; AD 2010-17-18]
RIN 2120-AA64

Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) to
supersede AD 2010-13-08, which applies to all Air Tractor, Inc. (Air
Tractor) Models AT-802 and AT-802A airplanes. AD 2010-13-08 currently
requires you to repetitively inspect (using the eddy current method)
the two outboard fastener holes in both of the wing main spar lower
caps at the center splice joint for cracks and repair or replace any
cracked spar cap. Since we issued 2010-13-08, we evaluated service
information issued by Air Tractor and determined we need to add
inspections, add modifications, and change the safe life for certain
serial number (SN) ranges. Consequently, this AD would retain the
actions of AD 2010-13-08 and would add inspections, add modifications,
and change the safe life for certain SN ranges. We are issuing this AD
to detect and correct cracks in the wing main spar lower cap at the
center splice joint, which could result in failure of the spar cap and
lead to wing separation and loss of control of the airplane.

DATES: This AD becomes effective on September 9, 2010.
On September 9, 2010, the Director of the Federal Register approved
the incorporation by reference of Snow Engineering Co. Service Letter
80GG, revised December 21, 2005; Snow Engineering Co. Service
Letter 284, dated October 4, 2009; Snow Engineering Co.
Service Letter 281, dated August 1, 2009; Snow Engineering Co.
Service Letter 245, dated April 25, 2005; Snow Engineering Co.
Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow
Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November
25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev.
A., dated January 7, 2009, listed in this AD.
As of April 21, 2006 (71 FR 19994, April 19, 2006), the Director of
the Federal Register approved the incorporation by reference of Snow
Engineering Co. Service Letter 240, dated September 30, 2004;
and Snow Engineering Co. Process Specification 197, page 1,
revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and
page 5, dated May 3, 2002, listed in this AD.
We must receive any comments on this AD by October 12, 2010.

ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
To get the service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-
5616; fax: (940) 564-5612; E-mail: airmail@airtractor.com; Internet:
https://www.airtractor.com.
To view the comments to this AD, go to https://www.regulations.gov.
The docket number is FAA-2010-0827; Directorate Identifier 2010-CE-029-
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

Since 2000, we have issued several ADs related to the wing spar
inspection and safe life on Air Tractor AT-400, AT-500, AT-600, and AT-
800 series airplanes.
In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66 FR 27014,
May 16, 2001) to lower the safe life for the wing lower spar cap on Air
Tractor AT-400, AT-500, and AT-800 series airplanes. This AD allowed
for inspection (using eddy current methods) of the wing lower spar cap
for airplanes that were at or over the lower safe life and for which
parts were not available. Later that same year, we revised that AD to
remove AT-800 series airplanes from the applicability that were
equipped with the factory-supplied computerized fire gate (part number
80540) and engaged in full-time firefighting.
In 2002, we issued AD 2002-11-05, Amendment 39-12766 (67 FR 37967,
May 31, 2002) that retained the actions for the AT-802 series airplanes
and further reduced the safe life for certain AT-400 series airplanes
and certain AT-500 series airplanes that either incorporate or have
incorporated Marburger winglets.
After receiving reports of fatigue cracking found on three Model
AT-802A airplanes that were below the reduced safe life established in
AD 2001-10-04, we issued AD 2006-08-09, Amendment 39-14565 (71 FR
27794, May 12, 2006). AD 2006-08-09 required repetitively inspecting
the two outboard fastener holes in both of the wing main spar lower
caps at the center splice joint for cracks and repairing or replacing
any cracked spar cap.
After issuing AD 2006-08-09, we determined the need to clarify the
affected SN applicability. Models AT-

[[Page 52256]]

802 and AT-802A share a common SN range. Sometimes service information
listed only one of the models with a starting or ending SN within a SN
range, depending on which model was produced with that specific SN,
even though the service information applied to both models. We
superseded AD 2006-08-09 and issued AD 2010-13-08, Amendment 39-16339
(75 FR 35616, June 23, 2010) to retain the actions from AD 2006-08-09,
clarify serial number applicability, and add an option of modifying the
wing main spar lower caps to extend the safe life limit.
After completing fatigue analysis on Models AT-802 and AT-802A
airplanes, Air Tractor issued service information that adds
inspections, adds modifications, and changes the safe life for certain
SN ranges. Since we issued 2010-13-08, we evaluated this new service
information and determined the need to add inspections, add
modifications, and change the safe life for certain SN ranges.
This condition, if not corrected, could result in failure of the
spar cap and lead to wing separation and loss of control of the
airplane.

Relevant Service Information

We reviewed the following service information from Snow Engineering
Co.:
Service Letter 80GG, revised December 21, 2005;
Service Letter 284, dated October 4, 2009;
Service Letter 281, dated August 1, 2009;
Service Letter 245, dated April 25, 2005;
Service Letter 240, dated September 30, 2004;
Process Specification 197, page 1, revised June
4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated
May 3, 2002;
Drawing Number 20995, Sheet 3, dated November 25, 2005;
Drawing Number 20995, Sheet 2, Rev. D., dated November 25,
2005; and
Drawing Number 20975, Sheet 4, Rev. A., dated January 7,
2009.
The service information describes procedures for the following
actions:
Inspection (repetitively) of the two outboard fastener
holes in both of the wing main spar lower caps at the center splice
joint for cracks;
Repair or replacement of any cracked spar cap; and
Modification option to extend the safe life limit.

FAA's Determination and Requirements of This AD

We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD requires
you to repetitively inspect (using the eddy current method) the two
outboard fastener holes in both of the wing main spar lower caps at the
center splice joint for cracks and repair or replace any cracked spar
cap.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate
adoption of this AD, 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 an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2010-0827;
Directorate Identifier 2010-CE-029-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this AD.

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
rulemaking action.

[[Page 52257]]

Regulatory Flexibility Determination

The Regulatory Flexibility Act of 1980 (Pub. L. 96-354) (RFA)
establishes as a principle of regulatory issuance that agencies shall
endeavor, consistent with the objective of the rule and of applicable
statutes, to fit regulatory and informational requirements to the scale
of the businesses, organizations, and governmental jurisdictions
subject to regulation.
To achieve that principle, the RFA requires agencies to solicit and
consider flexible regulatory proposals and to explain the rationale for
their actions. The RFA covers a wide-range of small entities, including
small businesses, not-for-profit organizations, and small governmental
jurisdictions.
Agencies must perform a review to determine whether a proposed or
final rule will have a significant economic impact on a substantial
number of small entities. In accordance with Section 608 of the
Regulatory Flexibility Act, an agency head may waive or delay
completion of some or all of the requirements of Section 603 by
providing a written finding that this final rule is being promulgated
in response to an emergency that makes compliance or timely compliance
with the provisions of Section 603 impracticable.
We are performing a review to determine whether this final rule AD
action will have a significant economic impact on a substantial number
of small entities. However, the immediate safety of flight conditions
of this AD action make compliance with the provisions of Section 603
impracticable. Our justification for immediate adoption of this rule,
and therefore of impracticability, is stated in FAA's Justification and
Determination of the Effective Date. After we determine whether this
final rule AD action has a significant economic impact on a substantial
number of small entities or not, we will publish in the Federal
Register our determination and, if required, our final regulatory
flexibility analysis.

Examining the AD Docket

You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at https://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

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 FAA amends 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)
2010-13-08, Amendment 39-16339 (75 FR 35616, June 23, 2010), and by
adding a new AD to read as follows:

2010-17-18 Air Tractor, Inc.: Amendment 39-16412; Docket No. FAA-
2010-0827; Directorate Identifier 2010-CE-029-AD.

Effective Date

(a) This AD becomes effective on September 9, 2010.

Affected ADs

(b) This AD supersedes AD 2010-13-08; Amendment 39-16339.

Applicability

(c) This AD affects Models AT-802 and AT-802A airplanes, all
serial numbers (SNs) beginning with -0001, that are:
(1) Certificated in any category;
(2) Engaged in agricultural dispersal operations, including
those airplanes that have been converted from fire fighting to
agricultural dispersal or airplanes that convert between fire
fighting and agricultural dispersal;
(3) Not equipped with the factory-supplied computerized fire
gate (part number (P/N) 80540); and
(4) Not engaged in only full-time fire fighting.

Subject

(d) Air Transport Association of America (ATA) Code 57: Wings.

Unsafe Condition

(e) This AD results from our determination that we need to
require the actions in the new service information to add
inspections, add modifications, and change the safe life for certain
SN ranges. We are issuing this AD to detect and correct cracks in
the wing main spar lower cap at the center splice joint, which could
result in failure of the spar cap and lead to wing separation and
loss of control of the airplane.

Compliance

(f) To address this problem for Models AT-802 and AT-802A
airplanes, SNs -0001 through -0091, you must do the following,
unless already done:

Table 1--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) Eddy current inspect for cracks Initially inspect upon accumulating Follow Snow Engineering Co. Process
the center splice joint outboard 1,700 hours time-in-service (TIS) Specification 197, page 1,
two fastener holes in both the left or within the next 50 hours TIS revised June 4, 2002; pages 2
and right wing main spar lower after April 21, 2006 (the effective through 4, dated February 23, 2001;
caps. date of AD 2006-08-09), whichever and page 5, dated May 3, 2002.
occurs later, and repetitively
thereafter at intervals not to
exceed 800 hours TIS. If, before
September 9, 2010 (the effective
date of this AD), you installed the
center splice plate and extended 8-
bolt splice blocks, use the
inspection compliance times found
in paragraph (f)(5) of this AD.

[[Page 52258]]

(2) If you find any cracks as a Before further flight after the Follow Snow Engineering Co. Service
result of any inspection required inspection where a crack was found. Letter 284, dated October
in paragraph (f)(1) of this AD, do If, before the airplane reaches a 4, 2009; Snow Engineering Co.
the following actions: total of 3,200 hours TIS, you Process Specification 197,
(i) For cracks that can be repaired, repair your airplane following page 1, revised June 4, 2002; pages
repair the airplane by doing the paragraph (f)(2)(i) of this AD, you 2 through 4, dated February 23,
following actions: must do the eddy current 2001; and page 5, dated May 3,
(A) Install center splice plate, P/N inspections following the 2002; Snow Engineering Co. Drawing
20997-2, and extended 8[dash]bolt compliance times found in paragraph Number 20995, Sheet 2, Rev. D.,
splice blocks, P/N 20985-1 & -2, (f)(5) of this AD. If, at 3,200 dated November 25, 2005; and Snow
and cold-work the lower spar cap hours TIS or after, you repair your Engineering Co. Service Letter
fastener holes; and airplane following paragraph 240, dated September 30,
(B) Eddy current inspect for cracks (f)(2)(i) of this AD, this repair 2004.
the center splice joint outboard terminates the inspection
two fastener holes in both the left requirements of paragraph (f)(1) of
and right wing main spar lower this AD.
caps. This eddy current inspection
is required as part of the
modification and is separate from
the inspections required in
paragraph (f)(1) of this AD.
(ii) For cracks that cannot be
repaired by incorporating the
modification specified above, do
the actions to replace the lower
spar caps and associated parts
listed following the procedures
identified in paragraph (f)(3) of
this AD.
(3) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service
caps, the web plates, the center of the following compliance times Letter 284, dated October
joint splice blocks and hardware, occurs first: 4, 2009; Snow Engineering Co.
and the wing attach angles and (A) Before further flight when Service Letter 80GG,
hardware, and install the steel web cracks are found that cannot be revised December 21, 2005; Snow
splice plate. This replacement repaired by incorporating the Engineering Co. Drawing Number
terminates the repetitive modification in paragraph (f)(2)(i) 20975, Sheet 4, Rev. A, dated
inspections required in paragraph of this AD; or January 7, 2009.
(f)(1) of this AD. (B) Before or when the airplane
reaches the wing main spar lower
cap safe life of a total of 4,100
hours TIS or within the next 50
hours TIS after September 9, 2010
(the effective date of this AD),
whichever occurs later.
(ii) After this replacement the new
spar safe life is 11,700 hours TIS.
If, before September 9, 2010 (the
effective date of this AD), an
airplane main spar lower cap was
replaced with P/N 21083-1/-2, the
spar safe life for that P/N spar
cap is 8,000 hours TIS until the
main spar lower cap is replaced
with P/N 21118-1/-2. The new spar
safe life for P/N 21118-1/-2 is
11,700 hours.
(iii) To extend the initial 4,100
hours TIS safe life of the wing
main spar lower cap to a total of
8,000 hours TIS, you may
incorporate the optional
modification specified in paragraph
(f)(4) of this AD.
(4) To extend the safe life of the Modify at whichever of the following Follow Snow Engineering Co. Service
wing main spar lower cap to a total compliance times occurs first: Letter 284, dated October
of 8,000 hours TIS, you may (A) Before further flight after any 4, 2009; Snow Engineering Co.
incorporate the following optional inspection required in paragraph Process Specification 197,
modification. This modification (f)(1) of this AD where a crack is page 1, revised June 4, 2002; pages
terminates the repetitive found. If you modify your airplane 2 through 4, dated February 23,
inspections required in paragraph before the airplane reaches a total 2001; and page 5, dated May 3,
(f)(1) of this AD, unless you of 3,200 hours TIS to repair cracks 2002; Snow Engineering Co. Drawing
performed the modification before as required in paragraph (f)(2)(i) Number 20995, Sheet 2, Rev. D.,
the airplane reaches a total of of this AD, you must do the eddy dated November 25, 2005; and Snow
3,200 hours TIS to repair cracks: current inspections following the Engineering Co. Service Letter
(i) Install center splice plate, P/N compliance times found in paragraph 240, dated September 30,
20997-2, and extended 8[dash]bolt (f)(5) of this AD. 2004.
splice blocks, P/N 20985-1 & -2,
and cold-work the lower spar cap
fastener holes; and

[[Page 52259]]

(ii) Eddy current inspect for cracks (B) Between 3,200 hours TIS and
the center splice joint outboard 4,100 hours TIS.
two fastener holes in both the left
and right wing main spar lower
caps. This eddy current inspection
is required as part of the
modification and is separate from
the inspections required in
paragraph (f)(1) of this AD.
----------------------------------------------------------------------------------------------------------------

(5) If, before September 9, 2010 (the effective date of this
AD) or as a result of performing the repair for cracks following
paragraph (f)(2) of this AD, you installed the center splice plate
and extended 8-bolt splice blocks, use the following table for
compliance times to do the eddy current inspections required in
paragraph (f)(1) of this AD. If you find any cracks as a result of
any inspection following the compliance times in the following
table, you must do the replacement action in paragraph (f)(2)(ii) of
this AD:

Table 2--Eddy Current Inspection Compliance Times
------------------------------------------------------------------------
Repetitively inspect
thereafter at
Condition of the airplane Initially inspect intervals not to
exceed
------------------------------------------------------------------------
(i) If the airplane has When the airplane 1,200 hours TIS
already had the center reaches a total of until the 8,000
splice plate and extended 2,400 hours TIS hours TIS spar
8[dash]bolt splice blocks after the replacement time.
installed at or after 3,200 modification or
hours TIS but the fastener within the next 100
holes have not been cold days after
worked, at any time you may September 9, 2010
cold work the fastener (the effective date
holes to terminate the of this AD),
repetitive inspection whichever occurs
requirements of this later.
paragraph.
(ii) Before reaching 3,200 When the airplane 1,200 hours TIS.
hours TIS, the airplane had reaches a total of Upon reaching 4,800
the center splice plate and 2,400 hours TIS hours TIS after the
extended 8-bolt splice after the modification,
blocks already installed modification or inspect
but the fastener holes have within the next 100 repetitively
not been cold worked. days after thereafter at
September 9, 2010 intervals not to
(the effective date exceed 600 hours
of this AD), TIS until the 8,000
whichever occurs hours TIS spar
later. replacement time.
(iii) Before reaching 3,200 When the airplane 600 hours TIS until
hours TIS, the airplane had reaches a total of the 8,000 hours TIS
the center splice plate and 4,800 hours TIS spar replacement
extended 8-bolt splice after the time.
blocks installed and the modification or
fastener holes have been within the next 100
cold worked. days after
September 9, 2010
(the effective date
of this AD),
whichever occurs
later.
------------------------------------------------------------------------

(g) To address this problem for AT-802 and AT-802A airplanes,
SNs -0092 through -0101, you must do the following, unless already
done:

Table 3--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) Eddy current inspect for cracks Initially inspect upon accumulating Follow Snow Engineering Co. Service
the center splice joint outboard 1,700 hours TIS or within the next Letter 284, dated October
two fastener holes in both the left 50 hours TIS after September 9, 4, 2009; and Snow Engineering Co.
and right wing main spar lower 2010 (the effective date of this Process Specification 197,
caps. AD), whichever occurs later, and page 1, revised June 4, 2002; pages
repetitively thereafter at 2 through 4, dated February 23,
intervals not to exceed 800 hours 2001; and page 5, dated May 3,
TIS. If the center splice plate, P/ 2002.
N 20994-2, is installed as ....................................
specified in paragraph (g)(4) of
this AD, do the repetitive
inspections at intervals not to
exceed 2,000 hours TIS.
(2) If you find any cracks as a Before further flight after the Follow Snow Engineering Co. Service
result of any inspection required inspection where a crack was found. Letter 284, dated October
by paragraph (g)(1) of this AD, do 4, 2009; and Snow Engineering Co.
the following actions. This repair Process Specification 197,
modification terminates the page 1, revised June 4, 2002; pages
repetitive inspections required in 2 through 4, dated February 23,
paragraph (g)(1) of this AD: 2001; and page 5, dated May 3,
(i) For cracks that can be repaired, 2002, Snow Engineering Co. Service
repair the airplane by doing the Letter 281, dated August
following actions: 1, 2009; and Snow Engineering Co.
(A) Install the 9-bolt splice blocks Drawing Number 20995, Sheet 3,
and cold-work the lower spar cap dated November 25, 2005.
fastener holes;

[[Page 52260]]

(B) Eddy current inspect for cracks
the center splice joint outboard
two fastener holes in both the left
and right wing main spar lower
caps. This eddy current inspection
is required as part of the repair
and is separate from the
inspections required in paragraph
(g)(1) of this AD; and
(C) Install the center splice plate,
P/N 20994-2, per paragraph (g)(4)
if not already installed.
(ii) For cracks that cannot be
repaired by doing the actions in
paragraph (g)(2)(i) of this AD,
replace the lower spar caps and
associated parts listed following
the procedures identified in
paragraph (g)(3) of this AD.
(3) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service
caps, the web plates, the center of the following compliance times Letter 284, dated October
joint splice blocks and hardware, occurs first: 4, 2009; Snow Engineering Co.
and the wing attach angles and (A) Before further flight when Service Letter 80GG,
hardware, and install the steel web cracks are found that cannot be revised December 21, 2005; Snow
splice plate. This replacement repaired by incorporating the Engineering Co. Drawing Number
terminates the repetitive modification in paragraph (g)(2)(i) 20975, Sheet 4, Rev. A, dated
inspections required in paragraph of this AD; or January 7, 2009.
(g)(1) of this AD. (B) Before or when the airplane
reaches the wing main spar lower
cap safe life of a total of 4,100
hours TIS or within the next 50
hours TIS after September 9, 2010
(the effective date of this AD),
whichever occurs later.
(ii) To extend the initial 4,100
hours TIS safe life of the wing
main spar lower cap to a total of
8,000 hours TIS, you may
incorporate the optional
modification specified in paragraph
(g)(4) of this AD.
(iii)After replacement of the old
spar with the new lower spar cap, P/
N 21118-1/-2, the new spar safe
life is 11,700 hours TIS.
(4) To extend the safe life of the Before the airplane reaches a total Follow Snow Engineering Co. Service
wing main spar lower cap to a total of 4,100 hours TIS. After Letter 284, dated October
of 8,000 hours TIS, you may installation of the center splice 4, 2009; Snow Engineering Co.
incorporate the following optional plate, P/N 20994-2, do the Process Specification 197,
modification: repetitive inspections required in page 1, revised June 4, 2002; pages
(i) Install center splice plate, P/N paragraph (g)(1) at intervals not 2 through 4, dated February 23,
20994-2, if not already installed to exceed 2,000 hours TIS. If as of 2001; and page 5, dated May 3,
as part of a repair, and cold-work September 9, 2010 (the effective 2002; Snow Engineering Co. Drawing
the lower spar cap fastener holes; date of this AD) you have already Number 20975, Sheet 4, Rev. A.,
and exceeded the 4,100 hours TIS dated January 7, 2009; and Snow
(ii) Eddy current inspect for cracks threshold for extending the safe Engineering Co. Service Letter
the center splice joint outboard life to 8,000 hours TIS, you may be 245, dated April 25, 2005.
two fastener holes in both the left eligible for an alternative method
and right wing main spar lower of compliance following paragraph
caps. This eddy current inspection (m) in this AD.
is required as part of the
modification and is separate from
the inspections required in
paragraph (g)(1) of this AD.
(5) If you find any cracks as a Before further flight after the Follow Snow Engineering Co. Service
result of any repetitive inspection inspection where a crack was found. Letter 284, dated October
required by paragraph (g)(4) of 4, 2009; and Snow Engineering Co.
this AD, do the following actions. Process Specification 197,
This repair modification terminates page 1, revised June 4, 2002; pages
the repetitive inspections required 2 through 4, dated February 23,
in paragraph (g)(4) of this AD: 2001; and page 5, dated May 3,
(i) For cracks that can be repaired, 2002, Snow Engineering Co. Service
repair the airplane by doing the Letter 281, dated August
following actions: 1, 2009; and Snow Engineering Co.
(A) Install the 9-bolt splice blocks Drawing Number 20995, Sheet 3,
and cold-work the lower spar cap dated November 25, 2005.
fastener holes; and

[[Page 52261]]

(h) To address this problem for AT-802 and AT-802A airplanes,
SNs -0102 through -0178, you must do the following, unless already
done:

Table 4--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) Do an initial eddy current Before the airplane reaches a total Follow Snow Engineering Co. Process
inspection for cracks of the center of 5,500 hours TIS or within the Specification 197, page 1,
splice joint outboard two fastener next 50 hours TIS after September revised June 4, 2002; pages 2
holes in both the left and right 9, 2010 (the effective date of this through 4, dated February 23, 2001;
wing main spar lower caps. After AD), whichever occurs later. and page 5, dated May 3, 2002; Snow
this initial inspection, you may do Engineering Co. Service Letter
the optional cold-working of the 245, dated April 25, 2005;
lower spar cap fastener holes to and Snow Engineering Co. Service
increase the hours TIS between Letter 284, dated October
repetitive inspections required in 4, 2009.
paragraph (h)(2) of this AD.
(2) Repetitively eddy current (i) For fastener holes that are Follow Snow Engineering Co. Process
inspect for cracks the center cold-worked: After the initial Specification 197, page 1,
splice joint outboard two fastener inspection, repetitively thereafter revised June 4, 2002; pages 2
holes in both the left and right inspect at intervals not to exceed through 4, dated February 23, 2001;
wing main spar lower caps. 2,200 hours TIS. and page 5, dated May 3, 2002; Snow
(ii) For fastener holes not cold- Engineering Co. Service Letter
worked: After the initial 284, dated October 4,
inspection, repetitively thereafter 2009; and (optional) Snow
inspect at intervals not to exceed Engineering Co. Service Letter
1,100 hours TIS. 245, dated April 25, 2005.
(3) If you find any cracks as a Before further flight after the Follow Snow Engineering Co. Service
result of any inspection required inspection where a crack was found. Letter 281, dated August
by paragraphs (h)(1) and (h)(2) of 1, 2009; and Snow Engineering Co.
this AD, do the following actions. Drawing Number 20995, Sheet 3,
This modification terminates the dated November 25, 2005.
repetitive inspections required in
paragraph (h)(1) and (h)(2) of this
AD:
(i) For cracks that can be repaired,
repair the airplane by doing the
following actions:
(A) Install the 9-bolt splice blocks
and cold-work the lower spar cap
fastener holes; and
(B) Eddy current inspect for cracks
the center splice joint outboard
two fastener holes in both the left
and right wing main spar lower
caps. This eddy current inspection
is required as part of the repair
and is separate from the
inspections required in paragraphs
(h)(1) and (h)(2) of this AD.
(ii) For cracks that cannot be
repaired by doing the actions in
paragraph (h)(3)(i) of this AD,
replace the lower spar caps and
associated parts listed following
the procedures in paragraph (h)(4)
of this AD.

[[Page 52262]]

(4) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service
caps, the web plates, the center of the following compliance times Letter 284, dated October
joint splice blocks and hardware, occurs first: 4, 2009; Snow Engineering Co.
and the wing attach angles and (A) Before further flight when Service Letter 80GG,
hardware, and install the steel web cracks are found that cannot be revised December 21, 2005; Snow
splice plate. This replacement repaired by incorporating the Engineering Co. Drawing Number
terminates the repetitive repair in paragraph (h)(3)(i) of 20975, Sheet 4, Rev. A, dated
inspections required in paragraphs this AD; or January 7, 2009.
(h)(1) and (h)(2) of this AD. (B) Before or when the airplane
reaches the wing main spar lower
cap safe life of a total of 8,000
hours TIS or within the next 50
hours TIS after September 9, 2010
(the effective date of this AD),
whichever occurs later.
(ii) After this replacement the
new spar safe life is 11,700
hours TIS.
----------------------------------------------------------------------------------------------------------------

(i) To address this problem for AT-802 and AT-802A airplanes,
SNs -0179 through -0269, you must do the following, unless already
done:

Table 5--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
Replace the wing main spar lower By the 8,000 hours TIS safe-life or Follow Snow Engineering Co. Service
caps, the web plates, the center within the next 50 hours TIS after Letter 284, dated October
joint splice blocks and hardware, September 9, 2010 (the effective 4, 2009; Snow Engineering Co.
and the wing attach angles and date of this AD), whichever occurs Service Letter 80GG,
hardware, and install the steel web later. After this replacement the revised December 21, 2005; Snow
splice plate. subsequent new spar safe life is Engineering Co. Drawing Number
11,700 hours TIS. 20975, Sheet 4, Rev. A, dated
January 7, 2009.
----------------------------------------------------------------------------------------------------------------

(j) To address this problem for AT-802 and AT-802A airplanes,
SNs -0270 and subsequent, you must do the following, unless already
done:

Table 6--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
Replace the wing main spar lower By the 11,700 hours TIS safe-life or Follow Snow Engineering Co. Service
caps, the web plates, the center within the next 50 hours TIS after Letter 284, dated October
joint splice blocks and hardware, September 9, 2010 (the effective 4, 2009; Snow Engineering Co.
and the wing attach angles and date of this AD), whichever occurs Service Letter 80GG,
hardware, and install the steel web later. After this replacement the revised December 21, 2005; Snow
splice plate. subsequent new spar safe life is Engineering Co. Drawing Number
11,700 hours TIS. 20975, Sheet 4, Rev. A, dated
January 7, 2009.
----------------------------------------------------------------------------------------------------------------

(k) Report any crack from any inspection required in paragraphs
(f), (g), or (h) of this AD within 10 days after the cracks are
found on the form in Figure 1 of this AD.
(1) Send your report to 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.
(2) The Office of Management and Budget (OMB) approved the
information collection requirements contained in this regulation
under the provisions of the Paperwork Reduction Act and assigned OMB
Control Number 2120-0056.

Special Permit Flight

(l) Under 14 CFR part 39.23, we are allowing special flight
permits for the purpose of compliance with this AD under the
following conditions:
(1) Only operate in day visual flight rules (VFR).
(2) Ensure that the hopper is empty.
(3) Limit airspeed to 135 miles per hour (mph) indicated
airspeed (IAS).
(4) Avoid any unnecessary g-forces.
(5) Avoid areas of turbulence.
(6) Plan the flight to follow the most direct route.

AD 2010-17-18 INSPECTION REPORT
[REPORT ONLY IF CRACKS ARE FOUND]
------------------------------------------------------------------------

------------------------------------------------------------------------
General Information
------------------------------------------------------------------------
1. Inspection Performed By: 2. Phone:
------------------------------------------------------------------------
3. Aircraft Model: 4. Aircraft Serial Number:
------------------------------------------------------------------------
5. Engine Model Number: 6. Aircraft Total Hours TIS:
------------------------------------------------------------------------

[[Page 52263]]

7. Wing Total Hours TIS: 8. Lower Spar Cap Hours TIS:
------------------------------------------------------------------------
Previous Inspection/Repair History
------------------------------------------------------------------------
9. Has the lower spar cap been If yes, an inspection has occurred:
inspected (eddy[dash]current, dye Date:------------------------
penetrant, magnetic particle, or Inspection Method:------------
ultrasound) before? Lower Spar Cap TIS:------------
[squ] Yes [squ] No Cracks found? [squ] Yes [squ] No
------------------------------------------------------------------------
10. Has there been any major repair If yes, specify (Description and
or alteration performed to the hours TIS):
spar cap?
[squ] Yes [squ] No
------------------------------------------------------------------------
Inspection for AD 2010-17-18
------------------------------------------------------------------------
11. Date of AD inspection: 11a. Cracks found:
Inspection Results: [squ] Left Hand [squ] Right Hand
------------------------------------------------------------------------
11b. Crack Length:------------ 11c. Does drilling hole to next
larger size remove all traces of
the crack(s)?
Location:------------ [squ] Yes [squ] No
------------------------------------------------------------------------
12d. Corrective Action Taken:
------------------------------------------------------------------------
Mail report (only if you find any cracks as a result of the inspection
for AD 2010-17-18) to: 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.
Figure 1

Alternative Methods of Compliance (AMOCs)

(m) 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: Andy
McAnaul, Aerospace Engineer, ASW-150, FAA San Antonio MIDO-43, 10100
Reunion Pl., Ste. 650, San Antonio, Texas 78216, phone: (210) 308-
3365, fax: (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.
(n) AMOCs approved for AD 2010-13-08 are not approved for this
AD.

Material Incorporated by Reference

(o) You must use Snow Engineering Co. Service Letter
80GG, revised December 21, 2005; Snow Engineering Co.
Service Letter 284, dated October 4, 2009; Snow Engineering
Co. Service Letter 281, dated August 1, 2009; Snow
Engineering Co. Service Letter 245, dated April 25, 2005;
Snow Engineering Co. Service Letter 240, dated September
30, 2004; Snow Engineering Co. Process Specification 197,
page 1, revised June 4, 2002; pages 2 through 4, dated February 23,
2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing
Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co.
Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and
Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated
January 7, 2009, 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
80GG, revised December 21, 2005; Snow Engineering Co.
Service Letter 284, dated October 4, 2009; Snow Engineering
Co. Service Letter 281, dated August 1, 2009; Snow
Engineering Co. Service Letter 245, dated April 25, 2005;
Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November
25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev.
D., dated November 25, 2005; and Snow Engineering Co. Drawing Number
20975, Sheet 4, Rev. A., dated January 7, 2009, under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On April 21, 2006 (71 FR 19994, April 19, 2006), the
Director of the Federal Register approved the incorporation by
reference of Snow Engineering Co. Service Letter 240, dated
September 30, 2004; and Snow Engineering Co. Process Specification
197, page 1, revised June 4, 2002; pages 2 through 4, dated
February 23, 2001; and page 5, dated May 3, 2002.
(3) For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; fax: (940) 564-5612; E-mail: airmail@airtractor.com;
Internet: https://www.airtractor.com.
(4) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(5) You may also review copies of the service information
incorporated by reference for this AD 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 August 11, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-20555 Filed 8-24-10; 8:45 am]
BILLING CODE 4910-13-P

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