Airworthiness Directives; M7 Aerospace LLC Airplanes, 34326-34330 [2015-14698]

Download as PDF 34326 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules in the levels of production necessary for Board membership for each unit. Section 1220.201(d) of the Order provides that at the end of each 3-year period, the Secretary must review the volume of production of each unit and adjust the boundaries of any unit and the number of Board members from each such unit as necessary to conform with the criteria set forth in § 1220.201(e): (1) To the extent practicable, States with annual average soybean production of less than 3,000,000 bushels shall be grouped into geographically contiguous units, each of which has a combined production level equal to or greater than 3,000,000 bushels, and each such group shall be entitled to at least one member on the Board; (2) units with at least 3,000,000 bushels, but fewer than 15,000,000 bushels shall be entitled to one board member; (3) units with 15,000,000 bushels or more but fewer than 70,000,000 bushels shall be entitled to two Board members; (4) units with 70,000,000 bushels or more but fewer than 200,000,000 bushels shall be entitled to three Board members; and (5) units with 200,000,000 bushels or more shall be entitled to four Board members. The Board was last reapportioned in 2012. The total Board membership increased from 69 to 70 members, with Mississippi gaining one additional member. The final rule was published in the Federal Register (74 FR 27467) on January 2, 2013. This change was effective with the 2013 appointments. Currently, the Board has 70 members representing 31 geographical units. This membership is based on average production levels for the years 2007– 2011 (excluding crops in years that production was the highest and that production was the lowest) as reported by USDA’s National Agricultural Statistics Service (NASS). This proposed rule would increase total membership on the Board from 70 to 73. Production data for years 2010– 2014 (excluding the crops in years in which production was the highest and in which production was the lowest) was gathered from NASS. This change would not affect the number of geographical units. The NASS information combines the production from the Western and Eastern Regions into one production data without distinguishing between the two regions. The NASS data does not support a change in membership for either region. As such, this proposed rule would leave the membership of both regions unchanged with one member each. This proposed rule would adjust representation on the Board as follows: Current representation Proposed representation 3 0 2 State 4 1 3 Missouri .................................................................................................................................................................... New Jersey .............................................................................................................................................................. Wisconsin ................................................................................................................................................................. Board adjustments as proposed by this rulemaking would become effective, if adopted, with the 2016 appointment process. List of Subjects in 7 CFR Part 1220 Administrative practice and procedure, Advertising, Agricultural research, Marketing agreements, Soybeans and soybean products, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, it is proposed that title 7, part 1220 be amended as follows: PART 1220–SOYBEAN PROMOTION, RESEARCH, AND CONSUMER INFORMATION 1. The authority citation for 7 CFR part 1220 continues to read as follows: ■ Authority: 7 U.S.C. 6301–6311 and 7 U.S.C. 7401. 2. In § 1220.201, paragraph (a), the table is revised to read as follows: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS ■ § 1220.201 Membership of board. (a) * * * Unit Number of members Illinois .................................... Iowa ...................................... Minnesota ............................. Indiana .................................. Nebraska .............................. VerDate Sep<11>2014 16:44 Jun 15, 2015 4 4 4 4 4 Jkt 235001 Number of members Unit Ohio ...................................... Missouri ................................ Arkansas ............................... South Dakota ........................ Kansas .................................. Michigan ............................... North Dakota ........................ Mississippi ............................ Wisconsin ............................. Louisiana .............................. Tennessee ............................ North Carolina ...................... Kentucky ............................... Pennsylvania ........................ Virginia .................................. Maryland ............................... Georgia ................................. South Carolina ...................... Alabama ................................ Delaware ............................... Texas .................................... Oklahoma ............................. New York .............................. New Jersey ........................... Eastern Region (Massachusetts, Connecticut, Florida, Rhode Island, Vermont, New Hampshire, Maine, West Virginia, District of Columbia, and Puerto Rico ............................ Western Region PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Number of members Unit 4 4 3 3 3 3 3 3 3 2 2 2 2 2 2 2 2 1 1 1 1 1 1 1 (Montana, Wyoming, Colorado, New Mexico, Idaho, Utah, Arizona, Washington, Oregon, Nevada, California, Hawaii, and Alaska) ....................... * * * * * Dated: June 11, 2015. Rex A. Barnes, Associate Administrator, Agricultural Marketing Service. [FR Doc. 2015–14708 Filed 6–15–15; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2207; Directorate Identifier 2015–CE–003–AD] RIN 2120–AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 1 1 E:\FR\FM\16JNP1.SGM 16JNP1 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules We propose to supersede Airworthiness Directive (AD) 97–02–02, which applies to certain Models SA26– AT, SA26–T, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227–AC (C– 26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227–DC (C–26B), and SA227–TT airplanes. AD 97–02–02 currently requires applying torque to the control column pitch bearing attaching nuts, inspecting the bearing assembly, inspecting the elevator control rod end bearing retainer/dust seals, and replacing or installing new parts as necessary. Since we issued AD 97–02– 02, an operator experienced a complete loss of elevator control because of failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. This proposed AD would prevent loss of pitch control, which if not corrected, could result in loss of airplane control. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 31, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766; Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329– 4148. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2207; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket VerDate Sep<11>2014 16:44 Jun 15, 2015 Jkt 235001 contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, FAA, ASW–143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308–3365; fax: (210) 308–3370; email: andrew.mcanaul@faa.gov. SUPPLEMENTARY INFORMATION: 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–2015–2207; Directorate Identifier 2015–CE–003–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 because 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 about this proposed AD. Discussion On January 6, 1997, we issued AD 97– 02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997), (‘‘AD 97–02– 02’’), for certain M7 Aerospace LLC Models SA26–AT, SA26–T, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227–AC (C–26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227– DC (C–26B), and SA227–TT airplanes. AD 97–02–02 requires applying torque to check the security of the control column pitch bearing attaching nuts, inspecting for any looseness or movement of the bearing assembly, and inspecting the elevator control rod end bearing retainer/dust seals for creasing. If any of these problems are evident, replace these parts, as well as install a new bolt and washer to the elevator control rod end bearing assembly at the walking beam connection. AD 97–02–02 resulted from reports of Fairchild SA227 series airplanes losing pitch control inflight. We issued AD 97–02–02 to prevent loss of pitch control, which if not corrected, could result in loss of airplane control. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 34327 Actions Since AD 97–02–02 Was Issued Since we issued AD 97–02–02, an operator experienced complete loss of elevator control due to failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. A follow-on inspection of the operator’s fleet revealed a variety of hardware installed. Some hardware matched the illustrated parts catalog (IPC), some matched the AD 97–02–02 configuration, and some matched neither of those configurations. When AD 97–02–02 was issued, the IPC was never revised to match the hardware configuration called out in AD 97–02–02 or in the service information associated with that AD. Because of the conflict between the AD and the IPC configurations, an airplane that was in compliance with the requirements of AD 97–02–02 could have had an incorrect hardware configuration installed during routine maintenance after complying with the AD. The IPC has been updated and corrected by M7 Aerospace, LLC. Also, since we issued AD 97–02–02, the manufacturer developed an improved design for the control column pivot bearing and support structure that terminates the repetitive torque check and replacement of control column pivot bearings. The manufacturer also issued new service information that adds the 10,000-hour time in service (TIS) repetitive replacement of the control column pivot bearing that is in the airworthiness limitations section (ALS) of the airplane maintenance manual (AMM) and (if this revision is mandated) requires the replacement of the pivot bearing with the improved design within 35,000 hours TIS that is in the supplemental inspections document (SID). Issue of the new service information, the revised IPC, and this proposed AD will eliminate the conflicts between AD 97–02–02, the service information, the IPC, the ALS, and the SID. Relevant Service Information Under 1 CFR 51 We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26–27–30– 046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service Bulletin No. 26–27–30–047, dated June 16, 1997; M7 Aerospace SA226 Series Service Bulletin No. 226–27–060 R2, dated December 5, 2014; Fairchild Aerospace SA226 Series Service Bulletin No. 226–27–061, dated June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227–27–041 R2, dated December 5, 2014; Fairchild E:\FR\FM\16JNP1.SGM 16JNP1 34328 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules Aircraft SA227 Series Service Bulletin No. 227–27–042, dated June 16, 1997; M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7–27–010 R2, dated December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category Service Bulletin No. CC7–27–011, dated June 16, 1997. The service information describes procedures for inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage, and replacing parts as necessary. The service information also adds a repetitive replacement of the control column pivot bearings at 10,000 hours TIS and requires replacement of the control column pivot bearing with the improved design within 35,000 hours TIS. This information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of the NPRM. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain none of the requirements of AD 97–02–02. This proposed AD would require inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage, and replacing parts as necessary. This proposed AD would also require a 10,000-hour TIS repetitive replacement of the control column pivot bearing and require replacement of the control column pivot bearing with the improved design within 35,000 hours TIS. Replacing the original control column pivot bearing with the improved design terminates the requirement to repetitively replace the original control column pivot bearing every 10,000 hours. Costs of Compliance We estimate that this proposed AD affects 360 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Cost on U.S. operators Action Labor cost Parts cost Inspection of torque on the control column pivot bearing. Control column pivot bearing replacement New designed control column pivot bearing replacement. Elevator rod end bolt replacement ............ 2 work-hours × $85 per hour = $170 ........ Not applicable ......... $170 $61,200 8 work-hours × $85 per hour = $680 ........ 20 work-hours × $85 per hour = $1,700 ... 300 .......................... 2,450 ....................... 980 4,150 352,800 1,494,000 4 work-hours × $85 per hour = $340 ........ 10 ............................ 350 126,000 Authority for This Rulemaking asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 16:44 Jun 15, 2015 Jkt 235001 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, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 97–02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997), and adding the following new AD: ■ M7 Aerospace: Docket No. FAA–2015–2207; Directorate Identifier 2015–CE–003–AD. (a) Comments Due Date The FAA must receive comments on this AD action by July 31, 2015. (b) Affected ADs This AD supersedes AD 97–02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997). (c) Applicability This AD applies to M7 Aerospace LLC Models SA26–AT, SA26–T, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227– AC (C–26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227–DC (C–26B), SA227–TT, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition AD 97–02–02 (62 FR 2552, January 17, 1997) (‘‘AD 97–02–02’’) resulted from reports of Fairchild SA227 series airplanes losing pitch control in-flight. This supersedure was prompted by an operator experiencing E:\FR\FM\16JNP1.SGM 16JNP1 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules complete loss of elevator control because of failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. We are issuing this AD to prevent loss of pitch control, which if not corrected, could result in loss of airplane control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. Models SA227–CC and SA227–DC, serial numbers 892, 893, and 895 and up, have the revised (modified) configuration. Since those airplanes are already in compliance, they do not have to do the actions in paragraphs (h) or (i) of this AD, including all subparagraphs. Those airplanes must still do the actions required in paragraph (j) of this AD, including all subparagraphs. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (g) Credit for Actions Accomplished in Accordance With Previous Service Information This AD allows credit for the control column pivot bearing torque check and initial replacement required in paragraph (i)(2) of this AD and the elevator rod bolt inspection and initial replacement required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done before the effective date of this AD, following the procedures specified in the Accomplishment Instructions of the applicable service information listed in paragraphs (g)(1) through (g)(4) of this AD: (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. CC7–27–010, original issue or revision 1. (2) M7 Aerospace SA227 Series Service Bulletin No. 227–27–041, original issue or revision 1. (3) M7 Aerospace SA226 Series Service Bulletin No. 226–27–060, original issue or revision 1. (4) M7 Aerospace SA26 Series Service Bulletin No. 26–27–30–046, original issue or revision 1. (h) Control Column Pivot Bearing Revised (Modified) Configuration (1) On or before the airplane accumulates a total of 35,000 hours time-in-service (TIS) or within the next 1,000 hours TIS after the effective date of this AD, whichever occurs later, you must revise (modify) the control column pivot bearing configuration with the improved design. Use the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the actions for paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in paragraph (j) of this AD, including all subparagraphs. (i) Fairchild Aircraft SA26 Series Service Bulletin No. 26–27–30–047, dated June 16, 1997; (ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226–27–061, dated June 16, 1997; (iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227–27–042, dated June 16, 1997; or VerDate Sep<11>2014 16:44 Jun 15, 2015 Jkt 235001 (iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7–27–011, dated June 16, 1997. (2) You may at any time before 35,000 hours TIS revise (modify) the control column pivot bearing configuration with the improved design to terminate the repetitive replacement of the original control column pivot bearing using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. This action terminates the requirements of paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in pargraph (j) of this AD, including all subparagraphs. (i) Torque Check or Replacement of the Control Column Pivot Bearing (1) Use the service information, as applicable, listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control column pivot bearing torque check or replacement at the applicable compliance times in paragraph (i)(2) or (i)(3) of this AD, including all subparagraphs: (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26–27–30–046 R2, dated December 5, 2014; (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226–27–060 R2, dated December 5, 2014; (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227–27–041 R2, dated December 5, 2014; or (iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7–27–010 R2, December 5, 2014. (2) For airplanes where the control column pivot bearing has been torque checked or replaced within the last 10,000 hours TIS before the effective date of this AD using the applicable service information listed in paragraph (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, do one of the following actions: (i) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after the effective date of this AD, whichever occurs later, and repetitively thereafter every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after the effective date of this AD, whichever occurs later, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs. (3) For airplanes where the control column pivot bearing has not been torque checked or PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 34329 replaced within the last 10,000 hours TIS before the effective date of this AD using the applicable service information listed in paragraphs (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, within the next 200 hours TIS after the effective date of this AD, torque check the control column pivot bearing following paragraph 2.A. of the service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (4) If nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions: (i) Before further flight and repetitively thereafter at intervals not to exceed every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Before further flight, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs. (5) If no nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions: (i) Within the next 1,000 hours TIS after the effective date of this AD, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Within the next 1,000 hours TIS after the effective date of this AD, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. (j) Inspect the Elevator Control Rod Ends and Hardware (1) Within the next 200 hours TIS after the effective date of this AD, inspect the elevator control rod ends and hardware for wear, creasing, or other damage and verify the elevator rod bolt and attachment hardware for correct configuration following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (2) If any damage is found during the inspection required in paragraph (j)(1) of this AD or the elevator rod bolt and attachment hardware does not match the correct configuration, before further flight, replace the elevator rod bolt, rod ends, and associated hardware following paragraph 2.D. E:\FR\FM\16JNP1.SGM 16JNP1 34330 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (3) Replace the elevator rod end bolt and associated hardware following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD at whichever of the following compliance times applies and repetitively thereafter at intervals not to exceed 10,000 hours TIS: (i) For airplanes where the elevator rod bolt has been replaced: Within the next 10,000 hours TIS after the last elevator rod bolt replacement or within the next 1,000 hours TIS after the effective date of this AD, whichever occurs later; or (ii) For airplanes where the elevator rod bolt has never been replaced: Within the next 200 hours TIS after the effective date of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (l) Related Information (1) For more information about this AD, contact Andrew McAnaul, Aerospace Engineer, FAA, ASW–143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308– 3365; fax: (210) 308–3370; email: andrew.mcanaul@faa.gov. (2) For service information identified in this AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766; Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. Issued in Kansas City, Missouri, on June 9, 2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14698 Filed 6–15–15; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:44 Jun 15, 2015 Jkt 235001 DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2134; or in person at the Docket Management Facility 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: David Enns, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4147; fax: (316) 946–4107; email: david.enns@faa.gov. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2015–2134; Directorate Identifier 2015–CE–012–AD] RIN 2120–AA64 Airworthiness Directives; B/E Aerospace Protective Breathing Equipment Part Number 119003–11 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain B/E Aerospace protective breathing equipment (PBE) that is installed on airplanes. This proposed AD was prompted by reports of a compromise in the vacuum seal of the pouch that contains the PBE. This proposed AD would require inspecting the PBE to determine if the pouch has the proper vacuum seal. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 31, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact B/E Aerospace, Inc., Commercial Aircraft Products Group, 10800 Pflumm Road, Lenexa, Kansas 66215; telephone: (913) 338–9800; fax: (913) 338–8419; Internet: www.beaerospace.com. You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2134. SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–2134; Directorate Identifier 2015– CE–012–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 because 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 about this proposed AD. Discussion We received a report of B/E Aerospace protective breathing equipment (PBE), part number 119003–11, catching fire when activated by a crew member during taxi aboard an Emirates Airline airplane. Following the PBE fire event and during the initial investigation, it was determined that a number of pouches containing the PBE that were installed in various airplanes had a compromised vacuum seal. A compromised seal in the pouch of a PBE results in degradation and possible contamination of the chemicals that provide oxygen during use. E:\FR\FM\16JNP1.SGM 16JNP1

Agencies

[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34326-34330]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14698]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 34327]]

SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-02-02, 
which applies to certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, 
SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), 
SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. AD 97-02-02 
currently requires applying torque to the control column pitch bearing 
attaching nuts, inspecting the bearing assembly, inspecting the 
elevator control rod end bearing retainer/dust seals, and replacing or 
installing new parts as necessary. Since we issued AD 97-02-02, an 
operator experienced a complete loss of elevator control because of 
failure of the bolt attaching the elevator control rod to the elevator 
walking beam under the cockpit floor. This proposed AD would prevent 
loss of pitch control, which if not corrected, could result in loss of 
airplane control. We are proposing this AD to correct the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by July 31, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: 
(210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com. You may view this referenced 
service information at the FAA, Small Airplane Directorate, 901 Locust, 
Kansas City, Missouri 64106. For information on the availability of 
this material at the FAA, call 816-329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2207; or in person at the Docket Management Facility 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 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, 
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, 
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: andrew.mcanaul@faa.gov.

SUPPLEMENTARY INFORMATION:

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-2015-2207; 
Directorate Identifier 2015-CE-003-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 because 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 about this proposed AD.

Discussion

    On January 6, 1997, we issued AD 97-02-02, Amendment 39-9886 (62 FR 
2552, January 17, 1997), (``AD 97-02-02''), for certain M7 Aerospace 
LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-TC, 
SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-
26B), and SA227-TT airplanes. AD 97-02-02 requires applying torque to 
check the security of the control column pitch bearing attaching nuts, 
inspecting for any looseness or movement of the bearing assembly, and 
inspecting the elevator control rod end bearing retainer/dust seals for 
creasing. If any of these problems are evident, replace these parts, as 
well as install a new bolt and washer to the elevator control rod end 
bearing assembly at the walking beam connection. AD 97-02-02 resulted 
from reports of Fairchild SA227 series airplanes losing pitch control 
in-flight. We issued AD 97-02-02 to prevent loss of pitch control, 
which if not corrected, could result in loss of airplane control.

Actions Since AD 97-02-02 Was Issued

    Since we issued AD 97-02-02, an operator experienced complete loss 
of elevator control due to failure of the bolt attaching the elevator 
control rod to the elevator walking beam under the cockpit floor. A 
follow-on inspection of the operator's fleet revealed a variety of 
hardware installed. Some hardware matched the illustrated parts catalog 
(IPC), some matched the AD 97-02-02 configuration, and some matched 
neither of those configurations.
    When AD 97-02-02 was issued, the IPC was never revised to match the 
hardware configuration called out in AD 97-02-02 or in the service 
information associated with that AD. Because of the conflict between 
the AD and the IPC configurations, an airplane that was in compliance 
with the requirements of AD 97-02-02 could have had an incorrect 
hardware configuration installed during routine maintenance after 
complying with the AD. The IPC has been updated and corrected by M7 
Aerospace, LLC.
    Also, since we issued AD 97-02-02, the manufacturer developed an 
improved design for the control column pivot bearing and support 
structure that terminates the repetitive torque check and replacement 
of control column pivot bearings.
    The manufacturer also issued new service information that adds the 
10,000-hour time in service (TIS) repetitive replacement of the control 
column pivot bearing that is in the airworthiness limitations section 
(ALS) of the airplane maintenance manual (AMM) and (if this revision is 
mandated) requires the replacement of the pivot bearing with the 
improved design within 35,000 hours TIS that is in the supplemental 
inspections document (SID). Issue of the new service information, the 
revised IPC, and this proposed AD will eliminate the conflicts between 
AD 97-02-02, the service information, the IPC, the ALS, and the SID.

Relevant Service Information Under 1 CFR 51

    We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service 
Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226 
Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014; 
Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated 
June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27-
041 R2, dated December 5, 2014; Fairchild

[[Page 34328]]

Aircraft SA227 Series Service Bulletin No. 227-27-042, dated June 16, 
1997; M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin 
No. CC7-27-010 R2, dated December 5, 2014; and Fairchild Aircraft SA227 
Series Commuter Category Service Bulletin No. CC7-27-011, dated June 
16, 1997. The service information describes procedures for inspecting 
for movement and correct torque of the elevator control pivot bearing, 
inspecting the elevator control rod for damage, and replacing parts as 
necessary. The service information also adds a repetitive replacement 
of the control column pivot bearings at 10,000 hours TIS and requires 
replacement of the control column pivot bearing with the improved 
design within 35,000 hours TIS. This information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of the NPRM.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain none of the requirements of AD 97-02-
02. This proposed AD would require inspecting for movement and correct 
torque of the elevator control pivot bearing, inspecting the elevator 
control rod for damage, and replacing parts as necessary. This proposed 
AD would also require a 10,000-hour TIS repetitive replacement of the 
control column pivot bearing and require replacement of the control 
column pivot bearing with the improved design within 35,000 hours TIS. 
Replacing the original control column pivot bearing with the improved 
design terminates the requirement to repetitively replace the original 
control column pivot bearing every 10,000 hours.

Costs of Compliance

    We estimate that this proposed AD affects 360 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                  Labor cost               Parts cost              product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of torque on the      2 work-hours x $85  Not applicable.............            $170         $61,200
 control column pivot bearing.    per hour = $170.
Control column pivot bearing     8 work-hours x $85  300........................             980         352,800
 replacement.                     per hour = $680.
New designed control column      20 work-hours x     2,450......................           4,150       1,494,000
 pivot bearing replacement.       $85 per hour =
                                  $1,700.
Elevator rod end bolt            4 work-hours x $85  10.........................             350         126,000
 replacement.                     per hour = $340.
----------------------------------------------------------------------------------------------------------------

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,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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

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) 
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding 
the following new AD:

M7 Aerospace: Docket No. FAA-2015-2207; Directorate Identifier 2015-
CE-003-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 31, 
2015.

(b) Affected ADs

    This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552, 
January 17, 1997).

(c) Applicability

    This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T, 
SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, 
SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-TT, all serial 
numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    AD 97-02-02 (62 FR 2552, January 17, 1997) (``AD 97-02-02'') 
resulted from reports of Fairchild SA227 series airplanes losing 
pitch control in-flight. This supersedure was prompted by an 
operator experiencing

[[Page 34329]]

complete loss of elevator control because of failure of the bolt 
attaching the elevator control rod to the elevator walking beam 
under the cockpit floor. We are issuing this AD to prevent loss of 
pitch control, which if not corrected, could result in loss of 
airplane control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done. Models SA227-CC and SA227-DC, serial numbers 
892, 893, and 895 and up, have the revised (modified) configuration. 
Since those airplanes are already in compliance, they do not have to 
do the actions in paragraphs (h) or (i) of this AD, including all 
subparagraphs. Those airplanes must still do the actions required in 
paragraph (j) of this AD, including all subparagraphs.

(g) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This AD allows credit for the control column pivot bearing 
torque check and initial replacement required in paragraph (i)(2) of 
this AD and the elevator rod bolt inspection and initial replacement 
required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done 
before the effective date of this AD, following the procedures 
specified in the Accomplishment Instructions of the applicable 
service information listed in paragraphs (g)(1) through (g)(4) of 
this AD:
    (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. 
CC7-27-010, original issue or revision 1.
    (2) M7 Aerospace SA227 Series Service Bulletin No. 227-27-041, 
original issue or revision 1.
    (3) M7 Aerospace SA226 Series Service Bulletin No. 226-27-060, 
original issue or revision 1.
    (4) M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-046, 
original issue or revision 1.

(h) Control Column Pivot Bearing Revised (Modified) Configuration

    (1) On or before the airplane accumulates a total of 35,000 
hours time-in-service (TIS) or within the next 1,000 hours TIS after 
the effective date of this AD, whichever occurs later, you must 
revise (modify) the control column pivot bearing configuration with 
the improved design. Use the applicable service information listed 
in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising 
(modifying) the configuration of the control column pivot bearing 
with the improved design terminates the actions for paragraph (i) of 
this AD, including all subparagraphs, but you must still complete 
the required actions in paragraph (j) of this AD, including all 
subparagraphs.
    (i) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997;
    (ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997;
    (iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997; or
    (iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7-
27-011, dated June 16, 1997.
    (2) You may at any time before 35,000 hours TIS revise (modify) 
the control column pivot bearing configuration with the improved 
design to terminate the repetitive replacement of the original 
control column pivot bearing using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. This action terminates the requirements of paragraph (i) of 
this AD, including all subparagraphs, but you must still complete 
the required actions in pargraph (j) of this AD, including all 
subparagraphs.

(i) Torque Check or Replacement of the Control Column Pivot Bearing

    (1) Use the service information, as applicable, listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control 
column pivot bearing torque check or replacement at the applicable 
compliance times in paragraph (i)(2) or (i)(3) of this AD, including 
all subparagraphs:
    (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014;
    (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014;
    (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014; or
    (iv) M7 Aerospace LLC SA227 Series Commuter Category Service 
Bulletin No. CC7-27-010 R2, December 5, 2014.
    (2) For airplanes where the control column pivot bearing has 
been torque checked or replaced within the last 10,000 hours TIS 
before the effective date of this AD using the applicable service 
information listed in paragraph (g)(1) through (g)(4) or (i)(1)(i) 
through (i)(1)(iv) of this AD, do one of the following actions:
    (i) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after the effective date of this AD, whichever occurs later, and 
repetitively thereafter every 10,000 hours TIS, replace the control 
column pivot bearing following paragraph 2.B. of the Accomplishment 
Instructions of the applicable service information listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
    (ii) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after the effective date of this AD, whichever occurs later, revise 
(modify) the control column pivot bearing configuration with the 
improved design using the applicable service information listed in 
paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising 
(modifying) the configuration of the control column pivot bearing 
with the improved design terminates the repetitive replacement of 
the original control column pivot bearing. No other actions are 
required for paragraph (i) of this AD, including all subparagraphs, 
but you must still complete the actions in paragraph (j) of this AD, 
including all subparagraphs.
    (3) For airplanes where the control column pivot bearing has not 
been torque checked or replaced within the last 10,000 hours TIS 
before the effective date of this AD using the applicable service 
information listed in paragraphs (g)(1) through (g)(4) or (i)(1)(i) 
through (i)(1)(iv) of this AD, within the next 200 hours TIS after 
the effective date of this AD, torque check the control column pivot 
bearing following paragraph 2.A. of the service information listed 
in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD.
    (4) If nut movement occurs during the torque check required in 
paragraph (i)(3) of this AD, do one of the following actions:
    (i) Before further flight and repetitively thereafter at 
intervals not to exceed every 10,000 hours TIS, replace the control 
column pivot bearing following paragraph 2.B. of the Accomplishment 
Instructions of the applicable service information listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
    (ii) Before further flight, revise (modify) the control column 
pivot bearing configuration with the improved design using the 
applicable service information listed in paragraphs (h)(1)(i) 
through (h)(1)(iv) of this AD. Revising (modifying) the 
configuration of the control column pivot bearing with the improved 
design terminates the repetitive replacement of the original control 
column pivot bearing. No other actions are required for paragraph 
(i) of this AD, including all subparagraphs, but you must still 
complete the actions in paragraph (j) of this AD, including all 
subparagraphs.
    (5) If no nut movement occurs during the torque check required 
in paragraph (i)(3) of this AD, do one of the following actions:
    (i) Within the next 1,000 hours TIS after the effective date of 
this AD, replace the control column pivot bearing following 
paragraph 2.B. of the Accomplishment Instructions of the applicable 
service information listed in paragraphs (i)(1)(i) through 
(i)(1)(iv) of this AD; or
    (ii) Within the next 1,000 hours TIS after the effective date of 
this AD, revise (modify) the control column pivot bearing 
configuration with the improved design using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. Revising (modifying) the configuration of the control 
column pivot bearing with the improved design terminates the 
repetitive replacement of the original control column pivot bearing.

(j) Inspect the Elevator Control Rod Ends and Hardware

    (1) Within the next 200 hours TIS after the effective date of 
this AD, inspect the elevator control rod ends and hardware for 
wear, creasing, or other damage and verify the elevator rod bolt and 
attachment hardware for correct configuration following paragraph 
2.D. of the Accomplishment Instructions of the applicable service 
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD.
    (2) If any damage is found during the inspection required in 
paragraph (j)(1) of this AD or the elevator rod bolt and attachment 
hardware does not match the correct configuration, before further 
flight, replace the elevator rod bolt, rod ends, and associated 
hardware following paragraph 2.D.

[[Page 34330]]

of the Accomplishment Instructions of the applicable service 
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD.
    (3) Replace the elevator rod end bolt and associated hardware 
following paragraph 2.D. of the Accomplishment Instructions of the 
applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD at whichever of the following 
compliance times applies and repetitively thereafter at intervals 
not to exceed 10,000 hours TIS:
    (i) For airplanes where the elevator rod bolt has been replaced: 
Within the next 10,000 hours TIS after the last elevator rod bolt 
replacement or within the next 1,000 hours TIS after the effective 
date of this AD, whichever occurs later; or
    (ii) For airplanes where the elevator rod bolt has never been 
replaced: Within the next 200 hours TIS after the effective date of 
this AD.

 (k) Alternative Methods of Compliance (AMOCs)

    (1) 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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the ACO, send it to the attention of the 
person identified in paragraph (l)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(l) Related Information

    (1) For more information about this AD, contact Andrew McAnaul, 
Aerospace Engineer, FAA, ASW-143 (c/o San Antonio MIDO), 10100 
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 
308-3365; fax: (210) 308-3370; email: andrew.mcanaul@faa.gov.
    (2) For service information identified in this AD, contact M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; 
phone: (210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com. You may 
view this referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
816-329-4148.

    Issued in Kansas City, Missouri, on June 9, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-14698 Filed 6-15-15; 8:45 am]
 BILLING CODE 4910-13-P