Airworthiness Directives; Taylorcraft Aviation, LLC A, B, and F Series Airplanes, 69630-69635 [E7-23860]

Download as PDF 69630 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules For the reasons discussed above, I certify this proposed regulation: 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Saab Aircraft AB: Docket No. FAA–2007– 0299; Directorate Identifier 2007–NM– 239–AD. Comments Due Date (a) We must receive comments by January 9, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Saab Model SAAB 2000 airplanes, all serial numbers, certificated in any category. rmajette on PROD1PC64 with PROPOSALS Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) in June 2001. In their Letters referenced 04/00/02/07/01– L296 dated March 4th, 2002 and 04/00/02/ 07/03–L024, dated February 3rd, 2003, the JAA (Joint Aviation Authorities) recommended the application of a similar regulation to the National Aviation Authorities (NAA). Under this regulation, all holders of type certificates for passenger transport aircraft VerDate Aug<31>2005 17:06 Dec 07, 2007 Jkt 214001 Actions and Compliance (f) Within 48 months after the effective date of this AD, unless already done, do Modification 6089 and all related investigative actions and applicable corrective actions, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–57–033, dated March 2, 2000; or Revision 01, dated March 31, 2000. Do all applicable related investigative and corrective actions before further flight. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. 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, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007–0167, dated June 15, 2007; Saab Service Bulletin 2000–57–033, dated March 2, 2000; and Saab Service Bulletin PO 00000 Frm 00007 Fmt 4702 2000–57–033, Revision 01, dated March 31, 2000; for related information. Issued in Renton, Washington, on November 30, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23869 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0286; Directorate Identifier 2007–CE–086–AD] RIN 2120–AA64 Airworthiness Directives; Taylorcraft Aviation, LLC A, B, and F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 with either a passenger capacity of 30 or more, or a payload capacity of 7,500 pounds (3402 kg) or more, which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks. This Airworthiness Directive (AD), which renders mandatory the modification [6089] of improving the sealing of Fuel Access Doors, is a consequence of the design review. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Sfmt 4702 SUMMARY: We propose to supersede Airworthiness Directive (AD) AD 2007– 16–14, which applies to all Taylorcraft Aviation, LLC (Taylorcraft) A, B, and F series airplanes. AD 2007–16–14 currently requires you to do an initial visual inspection of the left and right wing front and aft lift struts for cracks and corrosion and replace any cracked strut or strut with corrosion that exceeds certain limits. If the strut is replaced with an original design vented strut, AD 2007–16–14 requires you to repetitively inspect those struts thereafter. Since we issued AD 2007–16–14, we determined that the eddy current inspection method does not address the unsafe condition for the long term. We also determined that Models FA–III and TG–6 airplanes are not equipped with the affected struts. Consequently, this proposed AD would retain the actions required in AD 2007–16–14, except it removes the eddy current inspection method (provides 24month credit if already done using this method), adds the radiograph method as an inspection method, changes the Applicability section, and changes the compliance time between the repetitive inspections. We are issuing this proposed AD to detect and correct cracks and corrosion in the right and left wing front and aft lift struts. This condition, if not corrected, could result in failure of the lift strut and lead to inflight separation of the wing. DATES: We must receive comments on this proposed AD by January 9, 2008. E:\FR\FM\10DEP1.SGM 10DEP1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules Use one of the following addresses to comment on this proposed AD: • Federal eRulemaking Portal: Go to http://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. For service information identified in this proposed AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, Texas 78521; telephone: 956–986–0700. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, ADDRESSES: Texas 78216; telephone: (210) 308– 3365; fax: (210) 308–3370. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2007–0286; Directorate Identifier 2007–CE–086–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. 69631 Discussion Reports of several corroded vented wing lift struts from different Taylorcraft series airplanes caused us to issue AD 2007–16–14, Amendment 39– 15153 (72 FR 45153, August 13, 2007). AD 2007–16–14 currently requires the following on all Taylorcraft A, B, and F series airplanes: • Initial visual inspection of the left and right wing front and aft lift struts for cracks and corrosion; • Replacement of any cracked strut or strut with corrosion that exceeds certain limits with either sealed or vented struts; and • Repetitive eddy current or ultrasound inspection of any vented lift struts. Since issuing AD 2007–16–14, we received several comments concerning the AD. We reviewed all comments submitted to the docket. The following are significant comments that influenced our decision to propose superseding AD 2007–16–14 with a new AD: Comment FAA discussion We received several requests to use the radiograph inspection method as an alternative method of compliance (AMOC) for doing the repetitive strut inspection. We approved the radiograph inspection procedure as an AMOC for the repetitive inspections required in AD 2007–16–14, and the manufacturer has added the procedures for the radiograph inspection to their revised service bulletin. Based on the inspection methods used and the requirement to apply corrosion inhibitor to the strut interior at each inspection, we believe there is not an increased safety risk to the public by increasing the compliance time between the repetitive inspections from 24 months to 48 months for all airplanes. We do not have sufficient information to determine if a different inspection interval for land and float equipped airplanes is valid. We have approved using these parts as an AMOC to AD 2007–16–14. We received several requests to increase the compliance time between repetitive inspections because the Taylorcraft service information requires the application of corrosion inhibitor to the interior of the strut at each inspection. The commenters also requested a longer compliance time between repetitive inspections for land planes compared to float equipped planes. We received a request to use Univair part numbers (P/N) UA–A815 and UA–854 as a terminating action for the repetitive inspection requirement on Taylorcraft Models BC12–D/D1 and BCS12–D/D1 airplanes. We received several requests to install used vented lift struts that have been inspected using the criteria specified in paragraph (e)(2) of AD 2007–16–14. In addition to the comments above, we also received several reports of the following: • The eddy current inspection method currently required in AD 2007– We did not intend to preclude owners from installing these parts. Vented lift struts that are inspected using the ultrasound or radiograph inspection method, that meet the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, and that are treated with internal corrosion protection are considered new struts. 16–14 may not adequately address the unsafe condition for the long term; and • Models FA–III (Airphibian) and TG–6 Conversion airplanes do not have the affected struts installed. The following is a significant comment that did not influence our decision to propose superseding AD 2007–16–14 with a new AD: FAA discussion We received several requests to use the Maule Fabric Tester as an AMOC for doing the repetitive strut inspection. rmajette on PROD1PC64 with PROPOSALS Comment Testing of Taylorcraft strut samples with the Maule Fabric Tester shows that both 1025 steel material, and to a greater degree 4130 steel material, resist showing a positive dent indication until a major portion of the wall thickness is consumed. Taylorcraft used 4130 steel in a majority of their wing struts during production. We have not received any data substantiating that Taylorcraft wing struts can still carry required certification loads at the reduced strut wall material thickness indicated in the testing. VerDate Aug<31>2005 15:31 Dec 07, 2007 Jkt 214001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\10DEP1.SGM 10DEP1 69632 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules Cracks and corrosion in the right and left wing front and aft lift struts, if not detected and corrected, could result in failure of the wing lift strut and lead to in-flight separation of the wing. Relevant Service Information We reviewed Taylorcraft Aviation, LLC Service Bulletin (SB) No. 2007–001, Revision B, dated October 15, 2007. The service information describes procedures for wing lift strut assembly corrosion inspection and/or replacement. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would supersede AD 2007–16–14 with a new AD that would do the following: • Retain the actions of AD 2007–16– 14; • Remove the eddy current inspection method, but allow a 24-month credit for those who already inspected once using the eddy current method; • Remove Models FA–III (Airphibian) and TG–6 Conversion airplanes from the Applicability section; • Add the radiograph inspection method; • Increase the time interval between the repetitive inspections; • Allow the installation of Univair P/Ns UA–A815 and UA–854 on Taylorcraft Models BC12–D/D1 and BCS12–D/D1 airplanes as a terminating action for the repetitive inspection requirement; and • Allow the installation of used vented lift struts that have been inspected using ultrasound or radiograph inspection methods, meet the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, and have corrosion inhibitor applied to the interior of the strut. These lift struts are then subject to the repetitive 48-month inspection thereafter. We have determined that the Maule Fabric Tester is not a viable AMOC to this AD. This proposed AD would require you to use the service information described previously to perform these actions. Costs of Compliance We estimate that this proposed AD would affect 3,119 airplanes in the U.S. registry. We estimate the following costs to do the proposed visual inspection: Total cost per airplane Labor cost Parts cost 1 work-hour × $80 per hour = $80 ............................................................ Total cost on U.S. operators $80 $249,520 Not applicable .................................. We estimate the following costs to do the proposed repetitive ultrasound or radiograph inspection: Labor cost Parts cost 4 work-hours × $80 per hour = $320 ........................................................................... Total cost per airplane Not applicable ........................................... We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspections. We have no way of determining the number of airplanes that may need this replacement: Total cost per airplane to replace all 4 wing lift struts Labor cost Parts cost 4 work-hours to replace all 4 struts × $80 per hour = $320. Sealed front lift strut: $835 per strut. 2 per airplane = $1,670. Sealed aft lift strut: $638 per strut. 2 per airplane = $1,276. $1,670 + $1,276 + $320 = $3,266. Original design vented lift struts are no longer manufactured. We have no way of determining the cost associated with obtaining a useable vented strut. The estimated total cost on U.S. operators includes the cumulative costs associated with AD 2007–16–14 and any actions being added in this proposed AD. 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. Regulatory Findings Authority for This Rulemaking rmajette on PROD1PC64 with PROPOSALS $320 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 VerDate Aug<31>2005 15:31 Dec 07, 2007 Jkt 214001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; E:\FR\FM\10DEP1.SGM 10DEP1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at http://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. 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 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2007–16–14, Amendment 39–15153 (72 FR 45153, August 13, 2007), and by adding a new AD to read as follows: Taylorcraft Aviation, LLC: Docket No. FAA– 2007–0286; Directorate Identifier 2007– CE–086–AD. Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by January 9, 2008. Affected ADs (b) This AD supersedes AD 2007–16–14, Amendment 39–15153. 69633 P/N UA–A815 (for Models BC12–D/D1 and BCS12–D/D1 only), or FAA-approved equivalent P/N, and sealed aft lift struts, P/N MA–A854, Univair P/N UA–854 (for Models BC12–D/D1 and BCS12–D/D1 only), or FAA-approved equivalent P/N, for all struts. Note 1: This AD applies to all Taylorcraft models listed above, including those models not listed in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. If there are any other differences between this AD and the above service bulletin, this AD takes precedence. Note 2: For the purposes of this AD, a used strut that has been inspected using the ultrasound or radiograph inspection method, meets the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, and is treated with internal corrosion protection, is considered a new strut. Unsafe Condition Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Applicability (c) This AD applies to all serial numbers of Taylorcraft Models A, BC, BCS, BC–65, BCS–65, BC12–65 (Army L–2H), BCS12–65, BC12–D, BCS12–D, BC12–D1, BCS12–D1, BC12D–85, BCS12D–85, BC12D–4–85, BCS12D–4–85, (Army L–2G) BF, BFS, BF–60, BFS–60, BF–65, (Army L–2K) BF 12–65, BFS–65, BL, BLS, (Army L–2F) BL–65, BLS– 65, (Army L–2J) BL12–65, BLS12–65, 19, F19, F21, F21A, F21B, F22, F22A, F22B, and F22C airplanes that: (1) Are certificated in any category; and (2) Do not incorporate sealed wing front lift struts, part number (P/N) MA–A815, Univair Actions Compliance Procedures (1) Visually inspect the right and left wing front and aft lift struts, (P/N A–A815 and P/N A– A854, or FAA-approved equivalent P/Ns), along the entire bottom 12 inches of each strut for cracks and corrosion. Within the next 5 hours TIS after August 20, 2007 (the effective date of AD 2007–16– 14), unless one of the following conditions is met: (i) The struts have been replaced with parts specified in paragraph (e)(2)(i) of this AD. No further action is required on those struts. (ii) The struts have been replaced with parts specified in paragraph (e)(2)(ii) of this AD and have been installed for less than 48 months. No visual inspection is required. These parts are now subject to the repetitive inspection requirement specified in paragraph (e)(4) of this AD. Before further flight after the visual inspection required in paragraph (e)(1) of this AD. Follow Part 1 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007– 001, Revision A, dated August 1, 2007; or Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. rmajette on PROD1PC64 with PROPOSALS The Proposed Amendment (2) If any cracks are found during the visual inspection required in paragraph (e)(1) of this AD, replace the cracked strut with the following applicable strut: (i) A sealed front lift strut, P/N MA–A815, Univair P/N UA–A815 (for Models BC12–D/D1 and BCS12–D/D1 only), or FAA-approved equivalent P/N, a sealed aft lift strut, P/N MA–A854, Univair P/N UA–854 (for Models BC12–D/D1 and BCS12–D/D1 only), or FAA-approved equivalent P/N. Installing these lift struts terminates the repetitive inspections required by this AD for that strut and no further action is required. VerDate Aug<31>2005 17:06 Dec 07, 2007 Jkt 214001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 (d) This AD results from our determination that the radiograph inspection method should be used in place of the eddy current inspection method currently required in AD 2007–16–14. We are issuing this AD to detect and correct corrosion or cracks in the right and left wing front and aft lift struts, which could result in failure of the lift strut and lead to in-flight separation of the wing with consequent loss of control. Compliance (e) To address this problem, you must do the following, unless already done: Following the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. E:\FR\FM\10DEP1.SGM 10DEP1 69634 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules Actions Compliance rmajette on PROD1PC64 with PROPOSALS (ii) A new vented front lift strut, P/N A– A815, a new vented aft lift strut, P/N A– A854, or FAA-approved equivalent P/Ns, that is treated with internal corrosion protection specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. Installing one of these lift struts is subject to the repetitive inspections required in paragraph (e)(4) of this AD. (3) If corrosion is found during the inspection required in paragraph (e)(1) of this AD, do an ultrasound or radiograph inspection to determine if the corrosion exceeds the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. (4) If no corrosion or cracks are found during the visual inspection required in paragraph (e)(1) of this AD, or if the inspection required in paragraph (e)(3) reveals that the corrosion does not exceed the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, repetitively inspect thereafter using the ultrasound or radiograph inspection method and treat with internal corrosion protection until all struts are replaced with the sealed struts specified in paragraph (e)(2)(i) of this AD. If any cracks are found or corrosion is found that exceeds the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, during any of the repetitive inspections required by this AD, take the necessary corrective actions as applicable in paragraph (e)(5) of this AD. (5) If, during any inspection required in paragraphs (e)(3) or (e)(4) of this AD, any cracks are found or it is determined that the corrosion exceeds the Acceptance/Rejection Criteria specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007, replace the lift strut with the applicable lift strut specified in paragraph (e)(2)(i) or (e)(2)(ii) of this AD. (6) Do not install P/N A–A815, P/N A–A854, or FAA-approved equivalent P/N, unless: (i) within the last 48 months it has been inspected using the ultrasound or radiograph method; (ii) meets the Acceptance/Rejection Criteria; and (iii) is treated with internal corrosion protection as specified in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. VerDate Aug<31>2005 15:31 Dec 07, 2007 Jkt 214001 Procedures Before further flight after the visual inspection required in paragraph (e)(1) of this AD. Follow Part 2 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007– 001, Revision B, dated October 15, 2007. All ultrasound or radiograph inspections required by this AD must be done by one of the following: (i) A Level II or III inspector certified in the applicable ultrasound or radiograph inspection method using the guidelines established by the American Society of Nondestructive Testing or NAS 410 (formerly MIL–STD–410); (ii) An inspector certified to specific FAA or other acceptable government or industry standards, such as Air Transport Association (ATA) Specifications 105– Guidelines for Training and Qualifying Personnel in Nondestructive Testing Methods; or (iii) An FAA Repair Station or a Testing/ Inspection Laboratory qualified to do ultrasound or radiograph inspections. Follow Part 2 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007– 001, Revision B, dated October 15, 2007, using the ultrasound or radiograph inspection method. (i) Initially inspect within the next 3 months after August 20, 2007 (the effective date of AD 2007–16–14) or within 48 months after installing a lift strut specified in paragraph (e)(2)(ii) of this AD, whichever occurs later. (ii) Repetitively inspect thereafter at intervals not to exceed 48 months, except as required by paragraph (e)(4)(iii) of this AD. (iii) If the initial inspection was done using the eddy current method as specified in AD 2007–16–14, the first ultrasound or radiograph repetitive inspection must be done within the next 24 months after doing the eddy current inspection. Repetitively inspect thereafter at intervals not to exceed 48 months using the ultrasound or radiograph inspection method. Before further flight after the inspection required in paragraph (e)(3) or (e)(4) of this AD. Following the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007–001, Revision B, dated October 15, 2007. As of 5 hours TIS after the effective date of this AD. Not applicable. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\10DEP1.SGM 10DEP1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Proposed Rules 69635 Actions Compliance (7) As a terminating action for the repetitive inspections required by this AD, all vented lift struts (P/Ns A–A815, A–A854, and FAA-approved equivalent P/Ns) may be replaced with sealed lift struts (P/Ns MA–A815, UA– A815 (for Models BC12–D/D1 and BCS12– D/D1 only), MA–A854, UA–854 (for Models BC12–D/D1 and BCS12–D/D1 only), or FAAapproved equivalent P/Ns). At any time after the effective date of this AD Not applicable. 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; 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. (g) AMOCs approved for AD 2007–16–14 are approved for this AD. products listed above. This proposed 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 product. The MCAI describes the unsafe condition as: the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Related Information (h) To get copies of the service information referenced in this AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, Texas 78521; telephone: 956– 986–0700. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http://www.regulations.gov. Issued in Kansas City, Missouri, on December 3, 2007. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23860 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0298; Directorate Identifier 2007–NM–238–AD] RIN 2120–AA64 rmajette on PROD1PC64 with PROPOSALS Airworthiness Directives; Saab Model SAAB SF340A and Model SAAB 340B Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the VerDate Aug<31>2005 15:31 Dec 07, 2007 Jkt 214001 Procedures Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) * * * [which] required * * * [conducting] a design review against explosion risks. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by January 9, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0298; Directorate Identifier 2007–NM–238–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2007–0168, dated June 15, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) in June 2001. In their Letters referenced 04/00/02/07/01– L296 dated March 4, 2002 and 04/00/02/07/ 03–L024, dated February 3, 2003, the JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA). E:\FR\FM\10DEP1.SGM 10DEP1

Agencies

[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Proposed Rules]
[Pages 69630-69635]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23860]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0286; Directorate Identifier 2007-CE-086-AD]
RIN 2120-AA64


Airworthiness Directives; Taylorcraft Aviation, LLC A, B, and F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) AD 2007-
16-14, which applies to all Taylorcraft Aviation, LLC (Taylorcraft) A, 
B, and F series airplanes. AD 2007-16-14 currently requires you to do 
an initial visual inspection of the left and right wing front and aft 
lift struts for cracks and corrosion and replace any cracked strut or 
strut with corrosion that exceeds certain limits. If the strut is 
replaced with an original design vented strut, AD 2007-16-14 requires 
you to repetitively inspect those struts thereafter. Since we issued AD 
2007-16-14, we determined that the eddy current inspection method does 
not address the unsafe condition for the long term. We also determined 
that Models FA-III and TG-6 airplanes are not equipped with the 
affected struts. Consequently, this proposed AD would retain the 
actions required in AD 2007-16-14, except it removes the eddy current 
inspection method (provides 24-month credit if already done using this 
method), adds the radiograph method as an inspection method, changes 
the Applicability section, and changes the compliance time between the 
repetitive inspections. We are issuing this proposed AD to detect and 
correct cracks and corrosion in the right and left wing front and aft 
lift struts. This condition, if not corrected, could result in failure 
of the lift strut and lead to in-flight separation of the wing.

DATES: We must receive comments on this proposed AD by January 9, 2008.

[[Page 69631]]


ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to http://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.
    For service information identified in this proposed AD, contact 
Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, 
Texas 78521; telephone: 956-986-0700.

FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, 
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, 
Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2007-0286; Directorate Identifier 2007-CE-086-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    Reports of several corroded vented wing lift struts from different 
Taylorcraft series airplanes caused us to issue AD 2007-16-14, 
Amendment 39-15153 (72 FR 45153, August 13, 2007). AD 2007-16-14 
currently requires the following on all Taylorcraft A, B, and F series 
airplanes:
     Initial visual inspection of the left and right wing front 
and aft lift struts for cracks and corrosion;
     Replacement of any cracked strut or strut with corrosion 
that exceeds certain limits with either sealed or vented struts; and
     Repetitive eddy current or ultrasound inspection of any 
vented lift struts.
    Since issuing AD 2007-16-14, we received several comments 
concerning the AD. We reviewed all comments submitted to the docket. 
The following are significant comments that influenced our decision to 
propose superseding AD 2007-16-14 with a new AD:

------------------------------------------------------------------------
                Comment                           FAA discussion
------------------------------------------------------------------------
We received several requests to use the  We approved the radiograph
 radiograph inspection method as an       inspection procedure as an
 alternative method of compliance         AMOC for the repetitive
 (AMOC) for doing the repetitive strut    inspections required in AD
 inspection.                              2007-16-14, and the
                                          manufacturer has added the
                                          procedures for the radiograph
                                          inspection to their revised
                                          service bulletin.
We received several requests to          Based on the inspection methods
 increase the compliance time between     used and the requirement to
 repetitive inspections because the       apply corrosion inhibitor to
 Taylorcraft service information          the strut interior at each
 requires the application of corrosion    inspection, we believe there
 inhibitor to the interior of the strut   is not an increased safety
 at each inspection. The commenters       risk to the public by
 also requested a longer compliance       increasing the compliance time
 time between repetitive inspections      between the repetitive
 for land planes compared to float        inspections from 24 months to
 equipped planes.                         48 months for all airplanes.
                                          We do not have sufficient
                                          information to determine if a
                                          different inspection interval
                                          for land and float equipped
                                          airplanes is valid.
We received a request to use Univair     We have approved using these
 part numbers (P/N) UA-A815 and UA-854    parts as an AMOC to AD 2007-16-
 as a terminating action for the          14.
 repetitive inspection requirement on
 Taylorcraft Models BC12-D/D1 and BCS12-
 D/D1 airplanes.
We received several requests to install  We did not intend to preclude
 used vented lift struts that have been   owners from installing these
 inspected using the criteria specified   parts. Vented lift struts that
 in paragraph (e)(2) of AD 2007-16-14.    are inspected using the
                                          ultrasound or radiograph
                                          inspection method, that meet
                                          the Acceptance/Rejection
                                          Criteria specified in
                                          Taylorcraft Aviation, LLC
                                          Service Bulletin No. 2007-001,
                                          Revision B, dated October 15,
                                          2007, and that are treated
                                          with internal corrosion
                                          protection are considered new
                                          struts.
------------------------------------------------------------------------

    In addition to the comments above, we also received several reports 
of the following:
     The eddy current inspection method currently required in 
AD 2007-16-14 may not adequately address the unsafe condition for the 
long term; and
     Models FA-III (Airphibian) and TG-6 Conversion airplanes 
do not have the affected struts installed.
    The following is a significant comment that did not influence our 
decision to propose superseding AD 2007-16-14 with a new AD:

------------------------------------------------------------------------
                Comment                           FAA discussion
------------------------------------------------------------------------
We received several requests to use the  Testing of Taylorcraft strut
 Maule Fabric Tester as an AMOC for       samples with the Maule Fabric
 doing the repetitive strut inspection.   Tester shows that both 1025
                                          steel material, and to a
                                          greater degree 4130 steel
                                          material, resist showing a
                                          positive dent indication until
                                          a major portion of the wall
                                          thickness is consumed.
                                          Taylorcraft used 4130 steel in
                                          a majority of their wing
                                          struts during production. We
                                          have not received any data
                                          substantiating that
                                          Taylorcraft wing struts can
                                          still carry required
                                          certification loads at the
                                          reduced strut wall material
                                          thickness indicated in the
                                          testing.
------------------------------------------------------------------------


[[Page 69632]]

    Cracks and corrosion in the right and left wing front and aft lift 
struts, if not detected and corrected, could result in failure of the 
wing lift strut and lead to in-flight separation of the wing.

Relevant Service Information

    We reviewed Taylorcraft Aviation, LLC Service Bulletin (SB) No. 
2007-001, Revision B, dated October 15, 2007.
    The service information describes procedures for wing lift strut 
assembly corrosion inspection and/or replacement.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would supersede AD 2007-16-14 with a new AD that would do the 
following:
     Retain the actions of AD 2007-16-14;
     Remove the eddy current inspection method, but allow a 24-
month credit for those who already inspected once using the eddy 
current method;
     Remove Models FA-III (Airphibian) and TG-6 Conversion 
airplanes from the Applicability section;
     Add the radiograph inspection method;
     Increase the time interval between the repetitive 
inspections;
     Allow the installation of Univair P/Ns UA-A815 and UA-854 
on Taylorcraft Models BC12-D/D1 and BCS12-D/D1 airplanes as a 
terminating action for the repetitive inspection requirement; and
     Allow the installation of used vented lift struts that 
have been inspected using ultrasound or radiograph inspection methods, 
meet the Acceptance/Rejection Criteria specified in Taylorcraft 
Aviation, LLC Service Bulletin No. 2007-001, Revision B, dated October 
15, 2007, and have corrosion inhibitor applied to the interior of the 
strut. These lift struts are then subject to the repetitive 48-month 
inspection thereafter.
    We have determined that the Maule Fabric Tester is not a viable 
AMOC to this AD.
    This proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 3,119 airplanes in 
the U.S. registry.
    We estimate the following costs to do the proposed visual 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80..............  Not applicable..................             $80        $249,520
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed repetitive 
ultrasound or radiograph inspection:

------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                   Parts cost          airplane
------------------------------------------------------------------------
4 work-hours x $80 per hour = $320  Not applicable......            $320
------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of airplanes that 
may need this replacement:

------------------------------------------------------------------------
                                                        Total cost per
                                                          airplane to
           Labor cost                 Parts cost      replace all 4 wing
                                                          lift struts
------------------------------------------------------------------------
4 work-hours to replace all 4     Sealed front lift   $1,670 + $1,276 +
 struts x $80 per hour = $320.     strut: $835 per     $320 = $3,266.
                                   strut. 2 per
                                   airplane = $1,670.
                                  Sealed aft lift
                                   strut: $638 per
                                   strut. 2 per
                                   airplane = $1,276.
------------------------------------------------------------------------

    Original design vented lift struts are no longer manufactured. We 
have no way of determining the cost associated with obtaining a useable 
vented strut.
    The estimated total cost on U.S. operators includes the cumulative 
costs associated with AD 2007-16-14 and any actions being added in this 
proposed 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.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 69633]]

    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 2007-16-14, Amendment 39-15153 (72 FR 45153, August 13, 2007), and 
by adding a new AD to read as follows:

Taylorcraft Aviation, LLC: Docket No. FAA-2007-0286; Directorate 
Identifier 2007-CE-086-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by January 9, 2008.

Affected ADs

    (b) This AD supersedes AD 2007-16-14, Amendment 39-15153.

Applicability

    (c) This AD applies to all serial numbers of Taylorcraft Models 
A, BC, BCS, BC-65, BCS-65, BC12-65 (Army L-2H), BCS12-65, BC12-D, 
BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85, BCS12D-
4-85, (Army L-2G) BF, BFS, BF-60, BFS-60, BF-65, (Army L-2K) BF 12-
65, BFS-65, BL, BLS, (Army L-2F) BL-65, BLS-65, (Army L-2J) BL12-65, 
BLS12-65, 19, F19, F21, F21A, F21B, F22, F22A, F22B, and F22C 
airplanes that:
    (1) Are certificated in any category; and
    (2) Do not incorporate sealed wing front lift struts, part 
number (P/N) MA-A815, Univair P/N UA-A815 (for Models BC12-D/D1 and 
BCS12-D/D1 only), or FAA-approved equivalent P/N, and sealed aft 
lift struts, P/N MA-A854, Univair P/N UA-854 (for Models BC12-D/D1 
and BCS12-D/D1 only), or FAA-approved equivalent P/N, for all 
struts.

    Note 1: This AD applies to all Taylorcraft models listed above, 
including those models not listed in Taylorcraft Aviation, LLC 
Service Bulletin No. 2007-001, Revision B, dated October 15, 2007. 
If there are any other differences between this AD and the above 
service bulletin, this AD takes precedence.


    Note 2: For the purposes of this AD, a used strut that has been 
inspected using the ultrasound or radiograph inspection method, 
meets the Acceptance/Rejection Criteria specified in Taylorcraft 
Aviation, LLC Service Bulletin No. 2007-001, Revision B, dated 
October 15, 2007, and is treated with internal corrosion protection, 
is considered a new strut.

Unsafe Condition

    (d) This AD results from our determination that the radiograph 
inspection method should be used in place of the eddy current 
inspection method currently required in AD 2007-16-14. We are 
issuing this AD to detect and correct corrosion or cracks in the 
right and left wing front and aft lift struts, which could result in 
failure of the lift strut and lead to in-flight separation of the 
wing with consequent loss of control.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Visually inspect the right    Within the next 5   Follow Part 1 of
 and left wing front and aft       hours TIS after     the Instructions
 lift struts, (P/N A-A815 and P/   August 20, 2007     in Taylorcraft
 N A-A854, or FAA-approved         (the effective      Aviation, LLC
 equivalent P/Ns), along the       date of AD 2007-    Service Bulletin
 entire bottom 12 inches of each   16-14), unless      No. 2007-001,
 strut for cracks and corrosion.   one of the          Revision A, dated
                                   following           August 1, 2007;
                                   conditions is       or Taylorcraft
                                   met:                Aviation, LLC
                                  (i) The struts       Service Bulletin
                                   have been           No. 2007-001,
                                   replaced with       Revision B, dated
                                   parts specified     October 15, 2007.
                                   in paragraph
                                   (e)(2)(i) of this
                                   AD. No further
                                   action is
                                   required on those
                                   struts.
                                  (ii) The struts
                                   have been
                                   replaced with
                                   parts specified
                                   in paragraph
                                   (e)(2)(ii) of
                                   this AD and have
                                   been installed
                                   for less than 48
                                   months. No visual
                                   inspection is
                                   required. These
                                   parts are now
                                   subject to the
                                   repetitive
                                   inspection
                                   requirement
                                   specified in
                                   paragraph (e)(4)
                                   of this AD.
(2) If any cracks are found       Before further      Following the
 during the visual inspection      flight after the    Instructions in
 required in paragraph (e)(1) of   visual inspection   Taylorcraft
 this AD, replace the cracked      required in         Aviation, LLC
 strut with the following          paragraph (e)(1)    Service Bulletin
 applicable strut:                 of this AD.         No. 2007-001,
                                                       Revision B, dated
                                                       October 15, 2007.
    (i) A sealed front lift
     strut, P/N MA-A815, Univair
     P/N UA-A815 (for Models
     BC12-D/D1 and BCS12-D/D1
     only), or FAA-approved
     equivalent P/N, a sealed
     aft lift strut, P/N MA-
     A854, Univair P/N UA-854
     (for Models BC12-D/D1 and
     BCS12-D/D1 only), or FAA-
     approved equivalent P/N.
     Installing these lift
     struts terminates the
     repetitive inspections
     required by this AD for
     that strut and no further
     action is required.

[[Page 69634]]

 
    (ii) A new vented front lift
     strut, P/N A-A815, a new
     vented aft lift strut, P/N
     A-A854, or FAA-approved
     equivalent P/Ns, that is
     treated with internal
     corrosion protection
     specified in Taylorcraft
     Aviation, LLC Service
     Bulletin No. 2007-001,
     Revision B, dated October
     15, 2007. Installing one of
     these lift struts is
     subject to the repetitive
     inspections required in
     paragraph (e)(4) of this AD.
(3) If corrosion is found during  Before further      Follow Part 2 of
 the inspection required in        flight after the    the Instructions
 paragraph (e)(1) of this AD, do   visual inspection   in Taylorcraft
 an ultrasound or radiograph       required in         Aviation, LLC
 inspection to determine if the    paragraph (e)(1)    Service Bulletin
 corrosion exceeds the             of this AD.         No. 2007-001,
 Acceptance/Rejection Criteria                         Revision B, dated
 specified in Taylorcraft                              October 15, 2007.
 Aviation, LLC Service Bulletin                        All ultrasound or
 No. 2007-001, Revision B, dated                       radiograph
 October 15, 2007.                                     inspections
                                                       required by this
                                                       AD must be done
                                                       by one of the
                                                       following:
                                                      (i) A Level II or
                                                       III inspector
                                                       certified in the
                                                       applicable
                                                       ultrasound or
                                                       radiograph
                                                       inspection method
                                                       using the
                                                       guidelines
                                                       established by
                                                       the American
                                                       Society of
                                                       Nondestructive
                                                       Testing or NAS
                                                       410 (formerly MIL-
                                                       STD-410);
                                                      (ii) An inspector
                                                       certified to
                                                       specific FAA or
                                                       other acceptable
                                                       government or
                                                       industry
                                                       standards, such
                                                       as Air Transport
                                                       Association (ATA)
                                                       Specifications
                                                       105-Guidelines
                                                       for Training and
                                                       Qualifying
                                                       Personnel in
                                                       Nondestructive
                                                       Testing Methods;
                                                       or
                                                      (iii) An FAA
                                                       Repair Station or
                                                       a Testing/
                                                       Inspection
                                                       Laboratory
                                                       qualified to do
                                                       ultrasound or
                                                       radiograph
                                                       inspections.
(4) If no corrosion or cracks     (i) Initially       Follow Part 2 of
 are found during the visual       inspect within      the Instructions
 inspection required in            the next 3 months   in Taylorcraft
 paragraph (e)(1) of this AD, or   after August 20,    Aviation, LLC
 if the inspection required in     2007 (the           Service Bulletin
 paragraph (e)(3) reveals that     effective date of   No. 2007-001,
 the corrosion does not exceed     AD 2007-16-14) or   Revision B, dated
 the Acceptance/Rejection          within 48 months    October 15, 2007,
 Criteria specified in             after installing    using the
 Taylorcraft Aviation, LLC         a lift strut        ultrasound or
 Service Bulletin No. 2007-001,    specified in        radiograph
 Revision B, dated October 15,     paragraph           inspection
 2007, repetitively inspect        (e)(2)(ii) of       method.
 thereafter using the ultrasound   this AD,
 or radiograph inspection method   whichever occurs
 and treat with internal           later.
 corrosion protection until all   (ii) Repetitively
 struts are replaced with the      inspect
 sealed struts specified in        thereafter at
 paragraph (e)(2)(i) of this AD.   intervals not to
 If any cracks are found or        exceed 48 months,
 corrosion is found that exceeds   except as
 the Acceptance/Rejection          required by
 Criteria specified in             paragraph
 Taylorcraft Aviation, LLC         (e)(4)(iii) of
 Service Bulletin No. 2007-001,    this AD.
 Revision B, dated October 15,    (iii) If the
 2007, during any of the           initial
 repetitive inspections required   inspection was
 by this AD, take the necessary    done using the
 corrective actions as             eddy current
 applicable in paragraph (e)(5)    method as
 of this AD.                       specified in AD
                                   2007-16-14, the
                                   first ultrasound
                                   or radiograph
                                   repetitive
                                   inspection must
                                   be done within
                                   the next 24
                                   months after
                                   doing the eddy
                                   current
                                   inspection.
                                   Repetitively
                                   inspect
                                   thereafter at
                                   intervals not to
                                   exceed 48 months
                                   using the
                                   ultrasound or
                                   radiograph
                                   inspection method.
(5) If, during any inspection     Before further      Following the
 required in paragraphs (e)(3)     flight after the    Instructions in
 or (e)(4) of this AD, any         inspection          Taylorcraft
 cracks are found or it is         required in         Aviation, LLC
 determined that the corrosion     paragraph (e)(3)    Service Bulletin
 exceeds the Acceptance/           or (e)(4) of this   No. 2007-001,
 Rejection Criteria specified in   AD.                 Revision B, dated
 Taylorcraft Aviation, LLC                             October 15, 2007.
 Service Bulletin No. 2007-001,
 Revision B, dated October 15,
 2007, replace the lift strut
 with the applicable lift strut
 specified in paragraph
 (e)(2)(i) or (e)(2)(ii) of this
 AD.
(6) Do not install P/N A-A815, P/ As of 5 hours TIS   Not applicable.
 N A-A854, or FAA-approved         after the
 equivalent P/N, unless:           effective date of
                                   this AD.
    (i) within the last 48
     months it has been
     inspected using the
     ultrasound or radiograph
     method;
    (ii) meets the Acceptance/
     Rejection Criteria; and
    (iii) is treated with
     internal corrosion
     protection as specified in
     Taylorcraft Aviation, LLC
     Service Bulletin No. 2007-
     001, Revision B, dated
     October 15, 2007.

[[Page 69635]]

 
(7) As a terminating action for   At any time after   Not applicable.
 the repetitive inspections        the effective
 required by this AD, all vented   date of this AD.
 lift struts (P/Ns A-A815, A-
 A854, and FAA-approved
 equivalent P/Ns) may be
 replaced with sealed lift
 struts (P/Ns MA-A815, UA-A815
 (for Models BC12-D/D1 and BCS12-
 D/D1 only), MA-A854, UA-854
 (for Models BC12-D/D1 and BCS12-
 D/D1 only), or FAA-approved
 equivalent P/Ns).
------------------------------------------------------------------------

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; 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.
    (g) AMOCs approved for AD 2007-16-14 are approved for this AD.

Related Information

    (h) To get copies of the service information referenced in this 
AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, 
Brownsville, Texas 78521; telephone: 956-986-0700. To view the AD 
docket, go to U.S. Department of Transportation, Docket Operations, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey 
Avenue, SE., Washington, DC 20590, or on the Internet at http://www.regulations.gov.

    Issued in Kansas City, Missouri, on December 3, 2007.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-23860 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P