2015-19-10: Flight Controls

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [[Page 58356]] 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: 2015-19-10 M7 Aerospace: Amendment 39-18272; Docket No. FAA-2015- 2207; Directorate Identifier 2015-CE-003-AD. (a) Effective Date This AD is effective November 3, 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 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 November 3, 2015 (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) M7Aerospace 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 November 3, 2015 (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 paragraph (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 November 3, 2015 (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 thenext 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after November 3, 2015 (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 November 3, 2015 (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 November 3, 2015 (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 November 3, 2015 (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 [[Page 58357]] 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 November 3, 2015 (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 November 3, 2015 (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 November 3, 2015 (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. 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 November 3, 2015 (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 November 3, 2015 (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. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (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 December5, 2014. (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27- 041 R2, dated December 5, 2014. (iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7-27-010 R2, December 5, 2014. (v) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27- 30-047, dated June 16, 1997. (vi) Fairchild Aircraft SA226 Series Service Bulletin No. 226- 27-061, dated June 16, 1997. (vii) Fairchild Aircraft SA227 Series Service Bulletin No. 227- 27-042, dated June 16, 1997. (viii) Fairchild Aircraft SA227 Series Commuter Category No. CC7-27-011, dated June 16, 1997. (3) 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. (4) You may view this service information at 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.